Prospects for commercialization of SELV-based in-space operations

NASA Technical Reports Server (NTRS)

Katzberg, Stephen J. (Compiler); Garrison, James L., Jr. (Compiler)

1995-01-01

A workshop was hosted by the Langley Research Center as a part of an activity to assess the commercialization potential of Small Expendible Launch Vehicle-based in-space operations. Representatives of the space launch insurance industry, industrial consultants, producers of spacecraft, launch vehicle manufacturers, and government researchers constituted the participants. The workshop was broken into four sessions: Customers Small Expendible Launch Systems, Representative Missions, and Synthesis-Government role. This publication contains the presentation material, written synopses of the sessions, and conclusions developed at the workshop.

Study of extraterrestrial disposal of radioactive wastes. Part 1: Space transportation and destination considerations for extraterrestrial disposal of radioactive wastes. [feasibility of using space shuttle

NASA Technical Reports Server (NTRS)

Thompson, R. L.; Ramler, J. R.; Stevenson, S. M.

1974-01-01

A feasibility study of extraterrestrial disposal of radioactive waste is reported. This report covers the initial work done on only one part of the NASA study, that evaluates and compares possible space destinations and space transportation systems. The currently planned space shuttle was found to be more cost effective than current expendable launch vehicles by about a factor of 2. The space shuttle requires a third stage to perform the waste disposal missions. Depending on the particular mission, this third stage could be either a reusable space tug or an expendable stage such as a Centaur.

The development of a complementary expendable launch vehicle interface for an STS deployable payload

NASA Astrophysics Data System (ADS)

Eubanks, Ed; Gibb, John

1990-04-01

The development is described of an interface, the Titan Payload Adapter (TPA), between a Space Transportation System (STS) deployable payload and an expendable launch vehicle (ELV). Separate ascent and separation constraint systems allow a payload with integral trunnions to retain its originally designed, boost-phase load structure, yet also allow the expendable booster vehicle to separate from the payload via retro-rockets. Design requirements as well as development problems and their solutions are discussed.

The development of a complementary expendable launch vehicle interface for an STS deployable payload

NASA Technical Reports Server (NTRS)

Eubanks, ED; Gibb, John

1990-01-01

The development is described of an interface, the Titan Payload Adapter (TPA), between a Space Transportation System (STS) deployable payload and an expendable launch vehicle (ELV). Separate ascent and separation constraint systems allow a payload with integral trunnions to retain its originally designed, boost-phase load structure, yet also allow the expendable booster vehicle to separate from the payload via retro-rockets. Design requirements as well as development problems and their solutions are discussed.

Space Tug systems study. Volume 2: Compendium

NASA Technical Reports Server (NTRS)

1974-01-01

Possible storable propellant configurations and program plans are evaluated for the space tug. Alternatives examined include: use of existing expendable stages modified for use with shuttle, followed by a space tug at a later date; use of a modified growth version of existing expendable stages for greater performance and potential reuse, followed by a space tug at a later date; use of a low development cost, reusable, interim space tug available at shuttle initial operational capability (IOC) that could be evolved to greater system capabilities at a later date; and use a direct developed tug with maximum potential to be available at some specified time after space shuttle IOC. The capability options were narrowed down to three final options for detailed program definition.

14 CFR 1214.502 - Definitions.

Code of Federal Regulations, 2010 CFR

2010-01-01

... Aeronautics and Space NATIONAL AERONAUTICS AND SPACE ADMINISTRATION SPACE FLIGHT Mission Critical Space System Personnel Reliability Program § 1214.502 Definitions. (a) Mission Critical Space Systems. The Space Shuttle and other critical space systems, including Space Station Freedom, designated Expendable Launch...

Expendable vs reusable propulsion systems cost sensitivity

NASA Technical Reports Server (NTRS)

Hamaker, Joseph W.; Dodd, Glenn R.

1989-01-01

One of the key trade studies that must be considered when studying any new space transportation hardware is whether to go reusable or expendable. An analysis is presented here for such a trade relative to a proposed Liquid Rocket Booster which is being studied at MSFC. The assumptions or inputs to the trade were developed and integrated into a model that compares the Life-Cycle Costs of both a reusable LRB and an expendable LRB. Sensitivities were run by varying the input variables to see their effect on total cost. In addition a Monte-Carlo simulation was run to determine the amount of cost risk that may be involved in a decision to reuse or expend.

Environmental impact statement for the Kennedy Space Center, 1978 - 1979 revision

NASA Technical Reports Server (NTRS)

1979-01-01

The ongoing operation of KSC for expendable launch vehicles and automated spacecraft, continued development of facility capabilities, and the approved follow-on operations of the Space Transportation System and associated payloads are described. Emphasis is placed on the expendable launch vehicle and space shuttle traffic projected as of January, 1979. The maximum potential effect on the environment is addressed. Site specific environmental effects are summarized. It is indicated that all potential impacts will be localized, of short duration, controllable, and of minimum severity. The impact on land use, air and water quality, weather, and noise effects is covered.

14 CFR 1214.502 - Definitions.

Code of Federal Regulations, 2011 CFR

2011-01-01

... and other critical space systems, including Space Station Freedom, designated Expendable Launch... 14 Aeronautics and Space 5 2011-01-01 2010-01-01 true Definitions. 1214.502 Section 1214.502 Aeronautics and Space NATIONAL AERONAUTICS AND SPACE ADMINISTRATION SPACE FLIGHT Mission Critical Space System...

14 CFR 1214.502 - Definitions.

Code of Federal Regulations, 2013 CFR

2013-01-01

... and other critical space systems, including Space Station Freedom, designated Expendable Launch... 14 Aeronautics and Space 5 2013-01-01 2013-01-01 false Definitions. 1214.502 Section 1214.502 Aeronautics and Space NATIONAL AERONAUTICS AND SPACE ADMINISTRATION SPACE FLIGHT Mission Critical Space System...

14 CFR 1214.502 - Definitions.

Code of Federal Regulations, 2012 CFR

2012-01-01

... and other critical space systems, including Space Station Freedom, designated Expendable Launch... 14 Aeronautics and Space 5 2012-01-01 2012-01-01 false Definitions. 1214.502 Section 1214.502 Aeronautics and Space NATIONAL AERONAUTICS AND SPACE ADMINISTRATION SPACE FLIGHT Mission Critical Space System...

76 FR 72218 - National Environmental Policy Act; NASA Routine Payloads on Expendable Launch Vehicles

Federal Register 2010, 2011, 2012, 2013, 2014

2011-11-22

...; NASA Routine Payloads on Expendable Launch Vehicles AGENCY: National Aeronautics and Space... (CEQ) Regulations for Implementing the Procedural Provisions of NEPA (40 CFR parts 1500-1508), and NASA policy and procedures (14 CFR part 1216 subpart 1216.3), NASA has made a Finding of No Significant Impact...

Advanced Regenerative Environmental Control and Life Support Systems: Air and Water Regeneration

NASA Technical Reports Server (NTRS)

Schubert, F. H.; Wynveen, R. A.; Quattrone, P. D.

1985-01-01

Extended manned space missions will require regenerative life support techniques. Past manned missions used nonregenerative expendables, except for a molecular sieve based carbon dioxide removal system aboard Skylab. The resupply penalties associated with expendables becomes prohibitive as crew size and mission duration increase. The Space Station scheduled to be operational in the 1990's is based on a crew of four to sixteen and a resupply period of 90 days or greater. It will be the first major spacecraft to employ regenerable techniques for life support. The techniques to be used in the requirements for the space station are addressed.

Baseline spacecraft and mission design for the SP-100 flight experiment

NASA Technical Reports Server (NTRS)

Deininger, William D.; Vondra, Robert J.

1989-01-01

The design and performance of a spacecraft employing arcjet nuclear electric propulsion, suitable for use in the SP-100 Space Reactor Power System (SRPS) Flight Experiment, are outlined. The vehicle design is based on a 93 kWe ammonia arcjet system operating at an experimentally-measured specific impulse of 1030 s and an efficiency of 42 percent. The arcjet/gimbal assemblies, power conditioning subsystem, propellant feed system, propulsion system thermal control, spacecraft diagnostic instrumentation, and the telemetry requirements are described. A 100 kWe SRPS is assumed. The total spacecraft mass is baselined at 5675 kg excluding the propellant and propellant feed system. Four mission scenarios are described which are capable of demonstrating the full capability of the SRPS. The missions considered include spacecraft deployment to possible surveillance platform orbits, a spacecraft storage mission and an orbit raising round trip corresponding to possible orbit transfer vehicle missions. Launches from Kennedy Space Center using the Titan IV expendable launch vehicle are assumed.

Geosynchronous platform definition study. Volume 6: Geosynchronous program evaluation and recommendations

NASA Technical Reports Server (NTRS)

Myers, H. L.

1973-01-01

The programmatic analyses conducted to achieve the objectives of the study are presented. The characteristics are examined of alternate geosynchronous programs based on servicing concepts, geosynchronous platform configurations, and equipment definitions which have evolved during the study. The logistics support necessary to carry out programs using these systems is defined considering alternate approaches for on-orbit servicing. The costs of the resultant programs are then determined and the alternate program approaches compared. Conventional programs with expendable satellites are also defined to the extent necessary to permit comparison with on-orbit serviced platform programs.

KSC-98pc1191

NASA Image and Video Library

1998-09-30

KENNEDY SPACE CENTER, FLA. -- Deep Space 1 is lifted from its work platform, giving a closer view of the experimental solar-powered ion propulsion engine. The ion propulsion engine is the first non-chemical propulsion to be used as the primary means of propelling a spacecraft. Above the engine is one of the two solar wings, folded for launch, that will provide the power for it. When fully extended, the wings measure 38.6 feet from tip to tip. The first flight in NASA's New Millennium Program, Deep Space 1 is designed to validate 12 new technologies for scientific space missions of the next century. Another onboard experiment includes software that tracks celestial bodies so the spacecraft can make its own navigation decisions without the intervention of ground controllers. Deep Space 1 will complete most of its mission objectives within the first two months, but may also do a flyby of a near-Earth asteroid, 1992 KD, in July 1999. Deep Space 1 will be launched aboard a Boeing Delta 7326 rocket from Launch Pad 17A, Cape Canaveral Air Station, in October. Delta II rockets are medium capacity expendable launch vehicles derived from the Delta family of rockets built and launched since 1960. Since then there have been more than 245 Delta launches

KSC-98pc1189

NASA Image and Video Library

1998-09-30

KENNEDY SPACE CENTER, FLA. -- Deep Space 1 rests on its work platform after being fitted with thermal insulation. The reflective insulation is designed to protect the spacecraft as this side faces the sun. At either side of the spacecraft are its solar wings, folded for launch. When fully extended, the wings measure 38.6 feet from tip to tip. The first flight in NASA's New Millennium Program, Deep Space 1 is designed to validate 12 new technologies for scientific space missions of the next century. Onboard experiments include a solar-powered ion propulsion engine and software that tracks celestial bodies so the spacecraft can make its own navigation decisions without the intervention of ground controllers. The ion propulsion engine is the first non-chemical propulsion to be used as the primary means of propelling a spacecraft. Deep Space 1 will complete most of its mission objectives within the first two months, but may also do a flyby of a near-Earth asteroid, 1992 KD, in July 1999. Deep Space 1 will be launched aboard a Boeing Delta 7326 rocket from Launch Pad 17A, Cape Canaveral Air Station, in October. Delta II rockets are medium capacity expendable launch vehicles derived from the Delta family of rockets built and launched since 1960. Since then there have been more than 245 Delta launches

KSC-98pc1190

NASA Image and Video Library

1998-09-30

KENNEDY SPACE CENTER, FLA. -- Deep Space 1 rests on its work platform after being fitted with thermal insulation. The dark insulation is designed to protect the side of the spacecraft that faces away from the sun. At either side of the spacecraft are its solar wings, folded for launch. When fully extended, the wings measure 38.6 feet from tip to tip. The first flight in NASA's New Millennium Program, Deep Space 1 is designed to validate 12 new technologies for scientific space missions of the next century. Onboard experiments include a solar-powered ion propulsion engine and software that tracks celestial bodies so the spacecraft can make its own navigation decisions without the intervention of ground controllers. The ion propulsion engine is the first non-chemical propulsion to be used as the primary means of propelling a spacecraft. Deep Space 1 will complete most of its mission objectives within the first two months, but may also do a flyby of a near-Earth asteroid, 1992 KD, in July 1999. Deep Space 1 will be launched aboard a Boeing Delta 7326 rocket from Launch Pad 17A, Cape Canaveral Air Station, in October. Delta II rockets are medium capacity expendable launch vehicles derived from the Delta family of rockets built and launched since 1960. Since then there have been more than 245 Delta launches

Simple, Robust Cryogenic Propellant Depot for Near Term Applications

NASA Technical Reports Server (NTRS)

McLean, Christopher; Pitchford, Brian; Mustafi, Shuvo; Wollen, Mark; Walls, Laurie; Schmidt, Jeff

2011-01-01

The ability to refuel cryogenic propulsion stages on-orbit provides an innovative paradigm shift for space transportation supporting National Aeronautics and Space Administration s (NASA) Exploration program as well as deep space robotic, national security and commercial missions. Refueling enables large beyond low Earth orbit (LEO) missions without requiring super heavy lift vehicles that must continuously grow to support increasing mission demands as America s exploration transitions from early Lagrange point missions to near Earth objects (NEO), the lunar surface and eventually Mars. Earth-to-orbit launch can be optimized to provide competitive, cost-effective solutions that allow sustained exploration. This paper describes an experimental platform developed to demonstrate the major technologies required for fuel depot technology. This test bed is capable of transferring residual liquid hydrogen (LH2) or liquid oxygen (LO2) from a Centaur upper stage, and storage in a secondary tank for up to one year on-orbit. A dedicated, flight heritage spacecraft bus is attached to an Evolved Expendable Launch Vehicle (EELV) Secondary Payload Adapter (ESPA) ring supporting experiments and data collection. This platform can be deployed as early as Q1 2013. The propellant depot design described in this paper can be deployed affordably this decade supporting missions to Earth-Moon Lagrange points and lunar fly by. The same depot concept can be scaled up to support more demanding missions and launch capabilities. The enabling depot design features, technologies and concept of operations are described.

48 CFR 1828.371 - Clauses for cross-waivers of liability for Space Shuttle services, Expendable Launch Vehicle (ELV...

Code of Federal Regulations, 2012 CFR

2012-10-01

... Space Station activities and Science or Space Exploration activities unrelated to the International... Exploration activities unrelated to the International Space Station that involve a launch, NASA shall require... or Space Exploration Activities unrelated to the International Space Station, in solicitations and...

Comments on the commercialization of expendable launch vehicles

NASA Technical Reports Server (NTRS)

Trilling, D. R.

1984-01-01

The President's national space policy encourages private sector investment and involvement in civil space activities. Last November, the President designated the Department of Transportation as lead agency for the commercialization of expendable launch vehicles. This presents a substantial challenge to the United States Government, since the guidelines and requirements that are set now will have great influence on whether American firms can become a viable competitive industry in the world launch market. There is a dual need to protect public safety and free the private sector launch industry from needless regulatory barriers so that it can grow and prosper.

Expendable launch vehicle propulsion

NASA Technical Reports Server (NTRS)

Fuller, Paul N.

1991-01-01

The current status is reviewed of the U.S. Expendable Launch Vehicle (ELV) fleet, the international competition, and the propulsion technology of both domestic and foreign ELVs. The ELV propulsion technology areas where research, development, and demonstration are most needed are identified. These propulsion technology recommendations are based on the work performed by the Commercial Space Transportation Advisory Committee (COMSTAC), an industry panel established by the Dept. of Transportation.

The October 1973 expendable launch vehicle traffic model, revision 2

NASA Technical Reports Server (NTRS)

1974-01-01

Traffic model data for current expendable launch vehicles (assuming no space shuttle) for calendar years 1980 through 1991 are presented along with some supporting and summary data. This model was based on a payload program equivalent in scientific return to the October 1973 NASA Payload Model, the NASA estimated non NASA/non DoD Payload Model, and the 1971 DoD Mission Model.

The development status of candidate life support technology for a space station

NASA Technical Reports Server (NTRS)

Samonski, F. H., Jr.

1984-01-01

The establishment of a permanently-manned Space Station has recently been selected as the next major step in the U.S. space program. The requirements of a manned operations base in space appear to be best satisfied by on-board Environmental Control/Life Support Systems (ECLSS) which are free from, or have minimum dependence on, use of expendables and the frequent earth resupply missions which are part of systems using expendables. The present investigation is concerned with the range of regenerative life support system options which NASA is developing to be available for the Space Station designer. An air revitalization system is discussed, taking into account devices concerned with the carbon dioxide concentration, approaches of CO2 reduction, oxygen generation, trace contaminant control, and atmospheric quality monitoring. Attention is also given to an independent air revitalization system, nitrogen generation, a water reclamation system, a waste management system, applications of the technology, and future development requirements.

Access to Space : The Future of U.S. Space Transportation Systems

DOT National Transportation Integrated Search

1990-04-01

The United States now has an operating, mixed fleet comprised of reusable Space Shuttle orbiters and expendable launch vehicles (ELVs). The government and the private sector have invested in new launch technologies and established a fledgling private...

Space transportation and destination considerations for extraterrestrial disposal of radioactive waste

NASA Technical Reports Server (NTRS)

Zimmerman, A. V.; Thompson, R. L.; Lubick, R. J.

1973-01-01

A feasibility study is summarized of extraterrestrial (space) disposal of radioactive waste. The initial work on the evaluation and comparison of possible space destinations and launch vehicles is reported. Only current or planned space transportation systems were considered. The currently planned space shuttle was found to be more cost effective than current expendable launch vehicles, by about a factor of two. The space shuttle will require a third stage to perform the disposal missions. Depending on the particular mission this could be either a reusable space tug or an expendable stage such as a Centaur. Of the destinations considered, high earth orbits (between geostationary and lunar orbit altitudes), solar orbits (such as a 0.90 AU circular solar orbit) or a direct injection to solar system escape appear to be the best candidates. Both earth orbits and solar orbits have uncertainties regarding orbit stability and waste package integrity for times on the order of a million years.

Tether Deployer And Brake

NASA Technical Reports Server (NTRS)

Carroll, Joseph A.; Alexander, Charles M.

1993-01-01

Design concept promises speed, control, and reliability. Scheme for deploying tether provides for fast, free, and snagless payout and fast, dependable braking. Developed for small, expendable tethers in outer space, scheme also useful in laying transoceanic cables, deploying guidance wires to torpedoes and missiles, paying out rescue lines from ship to ship via rockets, deploying antenna wires, releasing communication and power cables to sonobuoys and expendable bathythermographs, and in reeling out lines from fishing rods.

Operations analysis (study 2.1). Payload designs for space servicing, addendum

NASA Technical Reports Server (NTRS)

Wolfe, R. R.

1974-01-01

Space replaceable units and payload configurations are revised to reflect increased levels of redundancy to be more consistent with current design practices. A reassessment of expendable payload design reliabilities was performed to provide a common basis for comparison with space serviceable configurations.

The Centaur G-Prime - Meeting mission needs today for tomorrow's space environment

NASA Astrophysics Data System (ADS)

Richardson, J. H.

1983-05-01

The performance history and capabilities, design features, and missions for the Centaur G-Prime upper stage for the STS are described. The Centaur has had 43 consecutive successes on expendable launch systems since 1971, and is equipped to transfer 13,500 lb from LEO to GEO. The vehicle dimensions include a 29.1 ft length, a 14.2 ft LH2 tank, and a 15 ft diameter designed for the Orbiter bay. It carries an avionics system that comprises a 16 K core memory computer, a four-gimballed platform inertial measurement group, a sequence control unit, a servo inverter unit, two remote multiplexing units, two signal conditioners, a telemetry system, batteries, etc. Twin RL-10 engines each furnish 16,500 lb of thrust. Near term missions for the Centaur include boosting the Galileo and Solar Polar Mission out of earth orbit towards their destination.

Manned systems utilization analysis (study 2.1). Volume 5: Program listing for the LOVES computer code

NASA Technical Reports Server (NTRS)

Wray, S. T., Jr.

1975-01-01

The LOVES computer code developed to investigate the concept of space servicing operational satellites as an alternative to replacing expendable satellites or returning satellites to earth for ground refurbishment is presented. In addition to having the capability to simulate the expendable satellite operation and the ground refurbished satellite operation, the program is designed to simulate the logistics of space servicing satellites using an upper stage vehicle and/or the earth to orbit shuttle. The program not only provides for the initial deployment of the satellite but also simulates the random failure and subsequent replacement of various equipment modules comprising the satellite. The program has been used primarily to conduct trade studies and/or parametric studies of various space program operational philosophies.

A mature Bosch CO2 reduction technology. [for long-duration space missions

NASA Technical Reports Server (NTRS)

King, C. D.; Holmes, R. F.

1976-01-01

The reduction of CO2 is one of the steps in closing the oxygen loop for long-duration manned space missions. Several units utilizing the Bosch process, which catalytically reduces CO2 with hydrogen, have been built and operated during the past decade. Each contributed substantial information affecting subsequent designs. Early challenges were primarily concerned with carbon control, materials durability, and reliability of reaction initiation. These were followed by concern about power consumption, expendable weight, volume, and process rate control. Suitable materials and techniques for carbon containment and process reliability have been demonstrated. Power requirements have been reduced by almost an order of magnitude. Methods for significant reductions in expendable weight and volume have been developed. The technology is at a state of maturity directly applicable to designs for space missions.

Expendable launch vehicle transportation for the space station

NASA Technical Reports Server (NTRS)

Corban, Robert R.

1988-01-01

Logistics transportation will be a critical element in determining the Space Station Freedom's level of productivity and possible evolutionary options. The current program utilizes the Space Shuttle as the only logistics support vehicle. Augmentation of the total transportation capability by expendable launch vehicles (ELVs) may be required to meet demanding requirements and provide for enhanced manifest flexibility. The total operational concept from ground operations to final return of support hardware or its disposal is required to determine the ELV's benefits and impacts to the Space Station Freedom program. The characteristics of potential medium and large class ELVs planned to be available in the mid-1990's (both U.S. and international partners' vehicles) indicate a significant range of possible transportation systems with varying degrees of operational support capabilities. The options available for development of a support infrastructure in terms of launch vehicles, logistics carriers, transfer vehicles, and return systems is discussed.

NASA's New Orbital Space Plane: A Bridge to the Future

NASA Technical Reports Server (NTRS)

Davis, Stephan R.; Engler, Leah M.; Fisher, Mark F.; Dumbacher, Dan L.; Boswell, Barry E.

2003-01-01

NASA is developing a new spacecraft system called the Orbital Space Plane (OSP). The OSP will be launched on an expendable launch vehicle and serve to augment the shuttle in support of the International Space Station by transporting astronauts to and from the International Space Station and by providing a crew rescue system.

From Earth to Orbit: An assessment of transportation options

NASA Technical Reports Server (NTRS)

Gavin, Joseph G., Jr.; Blond, Edmund; Brill, Yvonne C.; Budiansky, Bernard; Cooper, Robert S.; Demisch, Wolfgang H.; Hawk, Clark W.; Kerrebrock, Jack L.; Lichtenberg, Byron K.; Mager, Artur

1992-01-01

The report assesses the requirements, benefits, technological feasibility, and roles of Earth-to-Orbit transportation systems and options that could be developed in support of future national space programs. Transportation requirements, including those for Mission-to-Planet Earth, Space Station Freedom assembly and operation, human exploration of space, space science missions, and other major civil space missions are examined. These requirements are compared with existing, planned, and potential launch capabilities, including expendable launch vehicles (ELV's), the Space Shuttle, the National Launch System (NLS), and new launch options. In addition, the report examines propulsion systems in the context of various launch vehicles. These include the Advanced Solid Rocket Motor (ASRM), the Redesigned Solid Rocket Motor (RSRM), the Solid Rocket Motor Upgrade (SRMU), the Space Shuttle Main Engine (SSME), the Space Transportation Main Engine (STME), existing expendable launch vehicle engines, and liquid-oxygen/hydrocarbon engines. Consideration is given to systems that have been proposed to accomplish the national interests in relatively cost effective ways, with the recognition that safety and reliability contribute to cost-effectiveness. Related resources, including technology, propulsion test facilities, and manufacturing capabilities are also discussed.

Is It Worth It? - the Economics of Reusable Space Transportation

NASA Technical Reports Server (NTRS)

Webb, Richard

2016-01-01

Over the past several decades billions of dollars have been invested by governments and private companies in the pursuit of lower cost access to space through earth-to-orbit (ETO) space transportation systems. Much of that investment has been focused on the development and operation of various forms of reusable transportation systems. From the Space Shuttle to current efforts by private commercial companies, the overarching belief of those making such investments has been that reusing system elements will be cheaper than utilizing expendable systems that involve throwing away costly engines, avionics, and other hardware with each flight. However, the view that reusable systems are ultimately a "better" approach to providing ETO transportation is not held universally by major stakeholders within the space transportation industry. While the technical feasibility of at least some degree of reusability has been demonstrated, there continues to be a sometimes lively debate over the merits and drawbacks of reusable versus expendable systems from an economic perspective. In summary, is it worth it? Based on our many years of direct involvement with the business aspects of several expendable and reusable transportation systems, it appears to us that much of the discussion surrounding reusability is hindered by a failure to clearly define and understand the financial and other metrics by which the financial "goodness" of a reusable or expandable approach is measured. As stakeholders, the different users and suppliers of space transportation have a varied set of criteria for determining the relative economic viability of alternative strategies, including reusability. Many different metrics have been used to measure the affordability of space transportation, such as dollars per payload pound (kilogram) to orbit, cost per flight, life cycle cost, net present value/internal rate of return, and many others. This paper will examine the key considerations that influence stakeholders as they make space transportation investment decisions, including primary metrics by which various stakeholders measure financial goodness and other factors that significantly shape decisions to invest in reusable or expendable systems. It must be noted at the outset that reusable systems take many forms and perform different transportation functions including, but not limited to, ETO payload delivery. The discussion in this paper is limited to the economics of ETO transportation systems.

48 CFR 1852.228-78 - Cross-waiver of liability for NASA expendable launch vehicle launches.

Code of Federal Regulations, 2011 CFR

2011-10-01

... space exploration, use, and investment. The purpose of this clause is to extend this cross-waiver... Regulations System NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLAUSES AND FORMS SOLICITATION PROVISIONS AND... shall be broadly construed to achieve the objective of encouraging participation in space activities. (b...

Space shuttle phase B extension, volume 1

NASA Technical Reports Server (NTRS)

1971-01-01

In order to define a system which would significantly reduce payload delivery costs, activities were extended to modifications of the reusable space shuttle design concept. Considered were systems using orbiters with external propellant tanks and an interim expendable booster which allowed phased development of the usable orbiter and booster. Analyzed were: Merits of internal and external propellant tanks and the impact of external LH2 compared to L02 and LH2; impact of cargo bay size; impact abort; merit of expendable booster options; and merit of a phased development program. Studies showed that external L02/LH2 and the continued use of the J-2S engine on the orbiter reduced program cost and risk.

Deep Space 1 moves to CCAS for testing

NASA Technical Reports Server (NTRS)

1998-01-01

After covering the bulk of Deep Space 1 in thermal insulating blankets, workers in the Payload Hazardous Servicing Facility lift it from its work platform before moving it onto its transporter (behind workers at left). Deep Space 1 is being moved to the Defense Satellite Communications System Processing Facility (DPF), Cape Canaveral Air Station, for testing. At either side of the spacecraft are its solar wings, folded for launch. When fully extended, the winds measure 38.6 feet from tip to tip. The first flight in NASA's New Millennium Program, Deep Space 1 is designed to validate 12 new technologies for scientific space missions of the next century. Onboard experiments include a solar-powered ion propulsion engine and software that tracks celestial bodies so the spacecraft can make its own navigation decisions without the intervention of ground controllers. The ion propulsion engine is the first non-chemical propulsion to be used as the primary means of propelling a spacecraft. Deep Space 1 will complete most of its mission objectives within the first two months, but may also do a flyby of a near-Earth asteroid, 1992 KD, in July 1999. Deep Space 1 will be launched aboard a Boeing Delta 7326 rocket from Launch Pad 17A, Cape Canaveral Air Station, in October. Delta II rockets are medium capacity expendable launch vehicles derived from the Delta family of rockets built and launched since 1960. Since then there have been more than 245 Delta launches.

KSC-98pc1187

NASA Image and Video Library

1998-09-30

KENNEDY SPACE CENTER, FLA. -- After covering the bulk of Deep Space 1 in thermal insulating blankets, workers in the Payload Hazardous Servicing Facility lift it from its work platform before moving it onto its transporter (behind workers at left). Deep Space 1 is being moved to the Defense Satellite Communications System Processing Facility (DPF), Cape Canaveral Air Station, for testing. At either side of the spacecraft are its solar wings, folded for launch. When fully extended, the wings measure 38.6 feet from tip to tip. The first flight in NASA's New Millennium Program, Deep Space 1 is designed to validate 12 new technologies for scientific space missions of the next century. Onboard experiments include a solar-powered ion propulsion engine and software that tracks celestial bodies so the spacecraft can make its own navigation decisions without the intervention of ground controllers. The ion propulsion engine is the first non-chemical propulsion to be used as the primary means of propelling a spacecraft. Deep Space 1 will complete most of its mission objectives within the first two months, but may also do a flyby of a near-Earth asteroid, 1992 KD, in July 1999. Deep Space 1 will be launched aboard a Boeing Delta 7326 rocket from Launch Pad 17A, Cape Canaveral Air Station, in October. Delta II rockets are medium capacity expendable launch vehicles derived from the Delta family of rockets built and launched since 1960. Since then there have been more than 245 Delta launches

Payload Flight Assignments: NASA Mixed Fleet

NASA Technical Reports Server (NTRS)

Parker, Robert A. R.

1997-01-01

This manifest summarizes the missions planned by NASA for the Space Shuttle and Expendable Launch Vehicles (ELV's) as of the date of publication. Space Shuttle and ELV missions are shown through calendar year 2003. Space Shuttle missions for calendar years 2002-2003 are under review pending the resolution of details in the assembly sequence of the International Space Station (ISS).

Evolved Expendable Launch Vehicle: DOD Is Assessing Data on Worldwide Launch Market to Inform New Acquisition Strategy

DTIC Science & Technology

2016-07-22

Launch Services (ILS) of a Proton M launch vehicle and one provided by Space Exploration Technologies ( SpaceX ) of a Falcon 9 launch vehicle — and...U.S. based providers are United Launch Alliance (ULA), Space Exploration Technologies Corporation ( SpaceX ), and Orbital ATK. Countries we reviewed

Reusability Studies for Ares I and Ares V Propulsion

NASA Technical Reports Server (NTRS)

Williams, Thomas J.; Priskos, Alex S.; Schorr, Andrew A.; Barrett, Gregory

2008-01-01

With a mission to continue to support the goals of the International Space Station (ISS) and explore beyond Earth orbit, the United States National Aeronautics and Space Administration (NASA) is in the process of launching an entirely new space exploration initiative, the Constellation Program. Even as the Space Shuttle moves toward its final voyage, Constellation is building from nearly half a century of NASA spaceflight experience, and technological advances, including the legacy of Shuttle and earlier programs such as Apollo and the Saturn V rocket. Out of Constellation will come two new launch vehicles: the Ares I crew launch vehicle and the Ares V cargo launch vehicle. With the initial goal to seamlessly continue where the Space Shuttle leaves off, Ares will firstly service the Space Station. Ultimately, however, the intent is to push further: to establish an outpost on the Moon, and then to explore other destinations. With significant experience and a strong foundation in aerospace, NASA is now progressing toward the final design of the First Stage propulsion system for the Ares I. The new launch vehicle design will considerably increase safety and reliability, reduce the cost of accessing space, and provide a viable growth path for human space exploration. To achieve these goals, NASA is taking advantage of Space Shuttle hardware, safety, reliability, and experience. With efforts to minimize technical risk and life-cycle costs, the First Stage office is again pulling from NASA's strong legacy in aerospace exploration and development, most specifically the Space Shuttle Program. Trade studies have been conducted to evaluate lifecycle costs, expendability, and risk reduction. While many first stage features have already been determined, these trade studies are helping to resolve the operational requisites and configuration of the first stage element. This paper first presents an overview of the Ares missions and the genesis of the Ares vehicle design. It then looks at one of the most important trade studies to date, the "Ares I First Stage Expendability Trade Study." The purpose of this study was to determine the utility of flying the first stage as an expendable booster rather than making it reusable. To lower the study complexity, four operational scenarios (or cases) were defined. This assessment then included an evaluation of the development, reliability, performance, and transition impacts associated with an expendable solution. The paper looks at these scenarios from the perspectives of cost, reliability, and performance. The presentation provides an overview of the paper.

Reusability Studies for Ares I and Ares V Propulsion

NASA Technical Reports Server (NTRS)

Williams, Thomas J.; Priskos, Alex S.; Schorr, Andrew A.; Barrett, Greg

2008-01-01

With a mission to continue to support the goals of the International Space Station (ISS) and explore beyond Earth orbit, the United States National Aeronautics and Space Administration (NASA) is in the process of launching an entirely new space exploration initiative, the Constellation Program. Even as the Space Shuttle moves toward its final voyage, Constellation is building from nearly half a century of NASA spaceflight experience, and technological advances, including the legacy of Shuttle and earlier programs such as Apollo and the Saturn V rocket. Out of Constellation will come two new launch vehicles: the Ares I crew launch vehicle and the Ares V cargo launch vehicle. With the initial goal to seamlessly continue where the Space Shuttle leaves off, Ares will firstly service the Space Station. Ultimately, however, the intent is to push further: to establish an outpost on the Moon, and then to explore other destinations. With significant experience and a strong foundation in aerospace, NASA is now progressing toward the final design of the First Stage propulsion system for the Ares I. The new launch vehicle design will considerably increase safety and reliability, reduce the cost of accessing space, and provide a viable growth path for human space exploration. To achieve these goals, NASA is taking advantage of Space Shuttle hardware, safety, reliability, and experience. With efforts to minimize technical risk and life-cycle costs, the First Stage office is again pulling from NASA s strong legacy in aerospace exploration and development, most specifically the Space Shuttle Program. Trade studies have been conducted to evaluate life-cycle costs, expendability, and risk reduction. While many first stage features have already been determined, these trade studies are helping to resolve the operational requisites and configuration of the first stage element. This paper first presents an overview of the Ares missions and the genesis of the Ares vehicle design. It then looks at one of the most important trade studies to date, the "Ares I First Stage Expendability Trade Study." The purpose of this study was to determine the utility of flying the first stage as an expendable booster rather than making it reusable. To lower the study complexity, four operational scenarios (or cases) were defined. This assessment then included an evaluation of the development, reliability, performance, and transition impacts associated with an expendable solution. This paper looks at these scenarios from the perspectives of cost, reliability, and performance.

The Propulsive Small Expendable Deployer System (ProSEDS)

NASA Technical Reports Server (NTRS)

Lorenzini, Enrico C.; Estes, Robert D.; Cosmo, Mario L.

2001-01-01

This is the Annual Report #2 entitled "The Propulsive Small Expendable Deployer System (ProSEDS)" prepared by the Smithsonian Astrophysical Observatory for NASA Marshall Space Flight Center. This report covers the period of activity from 1 August 2000 through 30 July 2001. The topics include: 1) Updated System Performance; 2) Mission Analysis; 3) Updated Dynamics Reference Mission; 4) Updated Deployment Control Profiles and Simulations; 5) Comparison of ED tethers and electrical thrusters; 6) Kalman filters for mission estimation; and 7) Delivery of interactive software for ED tethers.

48 CFR 1852.228-78 - Cross-waiver of liability for NASA expendable launch vehicle launches.

Code of Federal Regulations, 2012 CFR

2012-10-01

... Damage Caused by Space Objects, entered into force on 1 September 1972, in which the person, entity, or... Regulations System NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLAUSES AND FORMS SOLICITATION PROVISIONS AND... parties related entities to encourage participation in space exploration, use, and investment. The purpose...

Operations analysis (study 2.1): Payload designs for space servicing

NASA Technical Reports Server (NTRS)

Wolfe, R. R.

1974-01-01

Potential modes of operating in space in the space shuttle era are documented. The October 1973 NASA Mission Model provides a definition of various NASA and non-DOD automated payload configurations when employed in an expendable mode. The model also specifies a launch schedule for initial deployment of payloads as well as for subsequent replacements at periodic cycles. This model and its associated payload definitions serve as a foundation for the data presented in this report. The reference model has been revised to reflect automated space servicing of payloads as an operational concept instead of the existing expendable approach. The indication is that the bulk of a payload's subsystems and mission equipment require no support over the lifetime of the program. However, failure of a single unit could result in loss of the mission objectives. When space servicing is employed, the approach is to replace only that unit causing the anomaly. This concept affords an opportunity to standardize space replacable units, as well as to reduce the expense of logistics support, by allowing multiple servicing on any single upper stage/shuttle flight.

Final design of a space debris removal system

NASA Technical Reports Server (NTRS)

Carlson, Erika; Casali, Steve; Chambers, Don; Geissler, Garner; Lalich, Andrew; Leipold, Manfred; Mach, Richard; Parry, John; Weems, Foley

1990-01-01

The objective is the removal of medium sized orbital debris in low Earth orbits. The design incorporates a transfer vehicle and a netting vehicle to capture the medium size debris. The system is based near an operational space station located at 28.5 degrees inclination and 400 km altitude. The system uses ground based tracking to determine the location of a satellite breakup or debris cloud. This data is unloaded to the transfer vehicle, and the transfer vehicle proceeds to rendezvous with the debris at a lower altitude parking orbit. Next, the netting vehicle is deployed, tracks the targeted debris, and captures it. After expending the available nets, the netting vehicle returns to the transfer vehicle for a new netting module and continues to capture more debris in the target area. Once all the netting modules are expended, the transfer vehicle returns to the space station's orbit, where it is resupplied with new netting modules from a space shuttle load. The new modules are launched by the shuttle from the ground, and the expended modules are taken back to Earth for removal of the captured debris, refueling, and repacking of the nets. Once the netting modules are refurbished, they are taken back into orbit for reuse. In a typical mission, the system has the ability to capture 50 pieces of orbital debris. One mission will take about six months. The system is designed to allow for a 30 degree inclination change on the outgoing and incoming trips of the transfer vehicle.

Final design of a space debris removal system

NASA Astrophysics Data System (ADS)

Carlson, Erika; Casali, Steve; Chambers, Don; Geissler, Garner; Lalich, Andrew; Leipold, Manfred; Mach, Richard; Parry, John; Weems, Foley

1990-12-01

The objective is the removal of medium sized orbital debris in low Earth orbits. The design incorporates a transfer vehicle and a netting vehicle to capture the medium size debris. The system is based near an operational space station located at 28.5 degrees inclination and 400 km altitude. The system uses ground based tracking to determine the location of a satellite breakup or debris cloud. This data is unloaded to the transfer vehicle, and the transfer vehicle proceeds to rendezvous with the debris at a lower altitude parking orbit. Next, the netting vehicle is deployed, tracks the targeted debris, and captures it. After expending the available nets, the netting vehicle returns to the transfer vehicle for a new netting module and continues to capture more debris in the target area. Once all the netting modules are expended, the transfer vehicle returns to the space station's orbit, where it is resupplied with new netting modules from a space shuttle load. The new modules are launched by the shuttle from the ground, and the expended modules are taken back to Earth for removal of the captured debris, refueling, and repacking of the nets. Once the netting modules are refurbished, they are taken back into orbit for reuse. In a typical mission, the system has the ability to capture 50 pieces of orbital debris. One mission will take about six months. The system is designed to allow for a 30 degree inclination change on the outgoing and incoming trips of the transfer vehicle.

EC/LSS thermal control system study for the space shuttle

NASA Technical Reports Server (NTRS)

Howell, H. R.

1972-01-01

The results of a parametric weight analysis of heat rejection systems for the space shuttle orbiter are presented. Integrating the suborbital heat rejection system with the overall heat rejection system design and the possible use of a common system for both on-orbit and suborbital operations require an overall system and parametric analyses applicable to all mission phases. The concept of equivalent weights, with weight penalties assigned for power, induced aircraft drag and radiator area is used to determine weight estimates for the following candidate systems: vapor cycle refrigeration, gas cycle refrigeration, radiators (space and atmospheric convectors), expendable heat sinks, and ram air. The orbiter power penalty, ram air penalty, and radiator weight penalty are analyzed. The vapor compression system and an expendable fluid system utilizing a multifluid spraying flash evaporator are selected as the two most promising systems. These are used for maximum on-orbit heat rejection in combination with or as a supplement to a space radiator.

Propulsive Small Expendable Deployer System (ProSEDS)

NASA Technical Reports Server (NTRS)

Curtis, Leslie; Johnson, Les; Brown, Norman S. (Technical Monitor)

2002-01-01

The Propulsive Small Expendable Deployer System (ProSEDS) space experiment will demonstrate the use of an electrodynamic tether propulsion system to generate thrust in space by decreasing the orbital altitude of a Delta 11 Expendable Launch Vehicle second stage. ProSEDS, which is planned on an Air Force GPS Satellite replacement mission in June 2002, will use the flight proven Small Expendable Deployer System (SEDS) to deploy a tether (5 km bare wire plus 10 km non-conducting Dyneema) from a Delta 11 second stage to achieve approx. 0.4N drag thrust. ProSEDS will utilize the tether-generated current to provide limited spacecraft power. The ProSEDS instrumentation includes Langmuir probes and Differential Ion Flux Probes, which will determine the characteristics of the ambient ionospheric plasma. Two Global Positioning System (GPS) receivers will be used (one on the Delta and one on the endmass) to help determine tether dynamics and to limit transmitter operations to occasions when the spacecraft is over selected ground stations. The flight experiment is a precursor to the more ambitious electrodynamic tether upper stage demonstration mission, which will be capable of orbit raising, lowering and inclination changes-all using electrodynamic thrust. An immediate application of ProSEDS technology is for the removal of spent satellites for orbital debris mitigation. In addition to the use of this technology to provide orbit transfer and debris mitigation it may also be an attractive option for future missions to Jupiter and any other planetary body with a magnetosphere.

Propulsive Small Expendable Deployer System (ProSEDS)

NASA Technical Reports Server (NTRS)

Ballance, Judy; Johnson, Les; Rogacki, John R. (Technical Monitor)

2000-01-01

The Propulsive Small Expendable Deployer System (ProSEDS) space experiment will demonstrate the use of an electrodynamic tether propulsion system to generate thrust in space by decreasing the orbital altitude of a Delta II Expendable Launch Vehicle (ELV) second stage. ProSEDS, which is planned to fly in 2001, will use the flight proven Small Expendable Deployer System (SEDS) to deploy a tether (5km bare wire plus 10 km spectra or dyneema) from a Delta II second stage to achieve approximately 0.4N drag thrust. ProSEDS will utilize the tether-generated current to provide limited spacecraft power. The ProSEDs instrumentation includes a Langmuir probe and Differential Ion Flux Probe, which will determine the characteristics of the ambient ionospheric plasma. Two Global Positioning System (GPS) receivers will be used (one on the Delta and one on the endmass) to help determine tether dynamics and to limit transmitter operations to occasions when the spacecraft is over selected ground stations, The flight experiment is a precursor to the more ambitious electrodynamic tether upper stage demonstration mission, which will be capable of orbit raising, lowering and inclination changes-all using electrodynamic thrust. An immediate application of ProSEDS technology is for the deorbit of spent satellites for orbital debris mitigation. In addition to the use of this technology to provide orbit transfer and debris mitigation it may also be an attractive option for future missions to Jupiter and any other planetary body with a magnetosphere.

RocketCam systems for providing situational awareness on rockets, spacecraft, and other remote platforms

NASA Astrophysics Data System (ADS)

Ridenoure, Rex

2004-09-01

Space-borne imaging systems derived from commercial technology have been successfully employed on launch vehicles for several years. Since 1997, over sixty such imagers - all in the product family called RocketCamTM - have operated successfully on 29 launches involving most U.S. launch systems. During this time, these inexpensive systems have demonstrated their utility in engineering analysis of liftoff and ascent events, booster performance, separation events and payload separation operations, and have also been employed to support and document related ground-based engineering tests. Such views from various vantage points provide not only visualization of key events but stunning and extremely positive public relations video content. Near-term applications include capturing key events on Earth-orbiting spacecraft and related proximity operations. This paper examines the history to date of RocketCams on expendable and manned launch vehicles, assesses their current utility on rockets, spacecraft and other aerospace vehicles (e.g., UAVs), and provides guidance for their use in selected defense and security applications. Broad use of RocketCams on defense and security projects will provide critical engineering data for developmental efforts, a large database of in-situ measurements onboard and around aerospace vehicles and platforms, compelling public relations content, and new diagnostic information for systems designers and failure-review panels alike.

An employee works on the top side of the experiment platform for the Huygens probe in the PHSF

NASA Technical Reports Server (NTRS)

1997-01-01

An employee in the Payload Hazardous Servicing Facility (PHSF) works on the top side of the experiment platform for the Huygens probe that will accompany the Cassini orbiter to Saturn during prelaunch processing, testing and integration in that facility. The Huygens probe and the Cassini orbiter being processed at KSC are the two primary components of the Cassini spacecraft, which will be launched on a Titan IVB/Centaur expendable launch vehicle from Cape Canaveral Air Station. Cassini will explore Saturn, its rings and moons for four years. The Huygens probe, designed and developed for the European Space Agency (ESA), will be deployed from the orbiter to study the clouds, atmosphere and surface of Saturn's largest moon, Titan. The orbiter was designed and assembled at NASA's Jet Propulsion Laboratory in California. Following postflight inspections, integration of the 12 science instruments not already installed on the orbiter will be completed. Then, the parabolic high-gain antenna and the propulsion module will be mated to the orbiter, followed by the Huygens probe, which will complete spacecraft integration. The Cassini mission is targeted for an Oct. 6 launch to begin its 6.7-year journey to the Saturnian system. Arrival at the planet is expected to occur around July 1, 2004.

Development and parametric evaluation of the prototype 2 and 3 flash evaporators

NASA Technical Reports Server (NTRS)

Hixon, C. W.; Dietz, J. B.

1975-01-01

Development of the Prototype 2 and 3 flash evaporator heat sinks which vaporize an expendable fluid to cool a heat transport fluid loop is reported. The units utilize Freon 21 as the heat transport fluid and water as the expendable fluid to meet the projected performance requirements of the space shuttle for both on-orbit and ascent/reentry operations. The evaporant is pulse-sprayed by on-off control onto heat transfer surfaces containing the transport fluid and exhausted to the vacuum environment through fixed area exhaust ducts.

Development of the Flight Tether for ProSEDS

NASA Technical Reports Server (NTRS)

Curtis, Leslie; Vaughn, Jason; Welzyn, Ken; Carroll, Joe; Brown, Norman S. (Technical Monitor)

2002-01-01

The Propulsive Small Expendable Deployer System (ProSEDS) space experiment will demonstrate the use of an electrodynamic tether propulsion system to generate thrust in space by decreasing the orbital altitude of a Delta 11 Expendable Launch Vehicle second stage. ProSEDS will use the flight-proven Small Expendable Deployer System to deploy a newly designed and developed tether which will provide tether generated drag thrust of approx. 0.4 N. The development and production of very long tethers with specific properties for performance and survivability will be required to enable future tether missions. The ProSEDS tether design and the development process may provide some lessons learned for these future missions. The ProSEDS system requirements drove the design of the tether to have three different sections of tether each serving a specialized purpose. The tether is a total of 15 kilometers long: 10 kilometers of a non-conductive Dyneema lead tether; 5 km of CCOR conductive coated wire; and 220 meters of insulated wire with a protective Kevlar overbraid. Production and joining of long tether lengths involved many development efforts. Extensive testing of tether materials including ground deployment of the full-length ProSEDS tether was conducted to validate the tether design and performance before flight.

76 FR 12403 - Office of Commercial Space Transportation; Notice of Availability of the Finding of No...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-03-07

... DEPARTMENT OF TRANSPORTATION Federal Aviation Administration Office of Commercial Space... Renewal of a Launch Operator License for Delta II Expendable Launch Vehicles at Cape Canaveral Air Force... United States Air Force (USAF) Medium Launch Vehicle Environmental Assessment (EA), Cape Canaveral Air...

Earth Science

NASA Image and Video Library

1994-04-12

The Atlas-1 (AC-77) that will loft the Geostationary Operational Environmental Satellite-J (GOES-J) next-generation advanced technology weather satellite into space sits poised for takeoff during final countdown operations at Cape Canaveral Air Station, Kennedy Space Center (KSC). GOES-J is atop the expendable launch vehicle inside the rocket's payload fairing.

Space shuttle environmental and thermal control life support system computer program

NASA Technical Reports Server (NTRS)

1972-01-01

A computer program for the design and operation of the space shuttle environmental and thermal control life support system is presented. The subjects discussed are: (1) basic optimization program, (2) off design performance, (3) radiator/evaporator expendable usage, (4) component weights, and (5) computer program operating procedures.

Comparative evaluation of existing expendable upper stages for space shuttle

NASA Technical Reports Server (NTRS)

Weyers, V. J.; Sagerman, G. D.; Borsody, J.; Lubick, R. J.

1974-01-01

The use of existing expendable upper stages in the space shuttle during its early years of operation is evaluated. The Burner 2, Scout, Delta, Agena, Transtage, and Centaur were each studied under contract by their respective manufacturers to determine the extent and cost of the minimum modifications necessary to integrate the stage with the shuttle orbiter. A comparative economic analysis of thirty-five different families of these stages is discussed. Results show that the overall transportation system cost differences between many of the families are quite small. However, by considering several factors in addition to cost, it is possible to select one family as being representative of the capability of the minimum modification existing stage approach. The selected family meets all of the specified mission requirements during the early years of shuttle operation.

Economic analysis of new space transportation systems: Executive summary

NASA Technical Reports Server (NTRS)

1971-01-01

An economic analysis of alternative space transportation systems is presented. Results indicate that the expendable systems represent modest investments, but the recurring costs of operation would remain high. The space shuttle and tug system requires a substantial investment, but would substantially reduce the recurring costs of operation. Economic benefits and costs of the different systems are also analyzed. Findings are summarized.

Space Station evolution study

NASA Technical Reports Server (NTRS)

Evans, David B.

1993-01-01

This is the Space Station Freedom (SSF) Evolution Study 1993 Final Report, performed under NASA Contract NAS8-38783, Task Order 5.1. This task examined: (1) the feasibility of launching current National Space Transportation System (NSTS) compatible logistics elements on expendable launch vehicles (ELV's) and the associated modifications, and (2) new, non-NSTS logistics elements for launch on ELV's to augment current SSF logistics capability.

Launch Vehicles

NASA Image and Video Library

1990-06-01

The Delta II expendable launch vehicle with the ROSAT (Roentgen Satellite), cooperative space X-ray astronomy mission between NASA, Germany and United Kingdom, was launched from the Cape Canaveral Air Force Station on June 1, 1990.

Space Station fluid management logistics

NASA Technical Reports Server (NTRS)

Dominick, Sam M.

1990-01-01

Viewgraphs and discussion on space station fluid management logistics are presented. Topics covered include: fluid management logistics - issues for Space Station Freedom evolution; current fluid logistics approach; evolution of Space Station Freedom fluid resupply; launch vehicle evolution; ELV logistics system approach; logistics carrier configuration; expendable fluid/propellant carrier description; fluid carrier design concept; logistics carrier orbital operations; carrier operations at space station; summary/status of orbital fluid transfer techniques; Soviet progress tanker system; and Soviet propellant resupply system observations.

Access to space study

NASA Technical Reports Server (NTRS)

1994-01-01

This report summarizes the results of a comprehensive NASA in-house study to identify and assess alternate approaches to access to space through the year 2030, and to select and recommend a preferred cause of action. The goals of the study were to identify the best vehicles and transportation architectures to make major reductions in the cost of space transportation (at least 50%), while at the same time increasing safety for flight crews by at least an order of magnitude. In addition, vehicle reliability was to exceed 0.98 percent, and, as important, the robustness, pad time, turnaround time, and other aspects of operability were to be vastly improved. This study examined three major optional architectures: (1) retain and upgrade the Space Shuttle and expendable launch vehicles; (2) develop new expendable vehicles using conventional technologies and transition from current vehicles beginning in 2005; and (3) develop new reusable vehicles using advanced technology, and transition from current vehicles beginning in 2008. The launch-needs, mission model utilized for for the study was based upon today's projection of civil, defense, and commercial mission payload requirements.

Expendable solid rocket motor upper stages for the Space Shuttle

NASA Technical Reports Server (NTRS)

Davis, H. P.; Jones, C. M.

1974-01-01

A family of expendable solid rocket motor upper stages has been conceptually defined to provide the payloads for the Space Shuttle with performance capability beyond the low earth operational range of the Shuttle Orbiter. In this concept-feasibility assessment, three new solid rocket motors of fixed impulse are defined for use with payloads requiring levels of higher energy. The conceptual design of these motors is constrained to limit thrusting loads into the payloads and to conserve payload bay length. These motors are combined in various vehicle configurations with stage components derived from other programs for the performance of a broad range of upper-stage missions from spin-stabilized, single-stage transfers to three-axis stabilized, multistage insertions. Estimated payload delivery performance and combined payload mission loading configurations are provided for the upper-stage configurations.

The applicability of DOE solar cell and array technology to space power

NASA Technical Reports Server (NTRS)

Scott-Monck, J. A.; Stella, P. M.; Berman, P. A.

1980-01-01

An evaluation of the main terrestrial photovoltaic development projects was performed. Technologies that may have applicability to space power are identified. Where appropriate, recommendations are made for programs to capitalize on developed technology. It is concluded that while the funding expended by DOE is considerably greater than the space (NASA and DOD) budget for photovoltaics, the terrestrial goals and the means for satisfying them are sufficiently different from space needs that little direct benefit currently exists for space applications.

48 CFR 35.017-7 - Limitation on the creation of new FFRDC's.

Code of Federal Regulations, 2013 CFR

2013-10-01

..., the Secretary of the Navy, the Secretary of the Air Force, the Secretary of Transportation, and the Administrator of the National Aeronautics and Space Administration may not obligate or expend amounts...

Autonomous rendezvous and docking operations of unmanned expendable cargo transfer vehicles (e.g. Centaur) with Space Station Freedom

NASA Technical Reports Server (NTRS)

Emmet, Brian R.

1991-01-01

This paper describes the results of the feasibility study using Centaur or other CTV's to deliver payloads to the Space Station Freedom (SSF). During this study was examined the requirements upon unmanned cargo transfer stages (including Centaur) for phasing, rendezvous, proximity operations and docking/berthing (capture).

A Comparison of Platforms for the Aerial Exploration of Titan

NASA Technical Reports Server (NTRS)

Wright, Henry S.; Gasbarre, Joseph F.; Levine, Joel S.

2005-01-01

Exploration of Titan, envisioned as a follow-on to the highly successful Cassini-Huygens mission, is described in this paper. A mission blending measurements from a dedicated orbiter and an in-situ aerial explorer is discussed. Summary description of the science rationale and the mission architecture, including the orbiter, is provided. The mission has been sized to ensure it can be accommodated on an existing expendable heavy-lift launch vehicle. A launch to Titan in 2018 with a 6-year time of flight to Titan using a combination of Solar Electric Propulsion and aeroassist (direct entry and aerocapture) forms the basic mission architecture. A detailed assessment of different platforms for aerial exploration of Titan has been performed. A rationale for the selection of the airship as the baseline platform is provided. Detailed description of the airship, its subsystems, and its operational strategies are provided.

KENNEDY SPACE CENTER, FLA. - In the Payload Hazardous Servicing Facility at KSC, installation is under way of the Mars Orbiter Camera (MOC) on the Mars Global Surveyor spacecraft. The MOC is one of a suite of six scientific instruments that will gather data about Martian topography, mineral distribution and weather during a two-year period. The Mars Global Surveyor is slated for launch aboard a Delta II expendable launch vehicle on Nov. 6, the beginning of a 20-day launch period.

NASA Image and Video Library

1996-08-19

KENNEDY SPACE CENTER, FLA. - In the Payload Hazardous Servicing Facility at KSC, installation is under way of the Mars Orbiter Camera (MOC) on the Mars Global Surveyor spacecraft. The MOC is one of a suite of six scientific instruments that will gather data about Martian topography, mineral distribution and weather during a two-year period. The Mars Global Surveyor is slated for launch aboard a Delta II expendable launch vehicle on Nov. 6, the beginning of a 20-day launch period.

Benefits of Government Incentives for Reusable Launch Vehicle Development

NASA Technical Reports Server (NTRS)

Shaw, Eric J.; Hamaker, Joseph W.; Prince, Frank A.

1998-01-01

Many exciting new opportunities in space, both government missions and business ventures, could be realized by a reduction in launch prices. Reusable launch vehicle (RLV) designs have the potential to lower launch costs dramatically from those of today's expendable and partially-expendable vehicles. Unfortunately, governments must budget to support existing launch capability, and so lack the resources necessary to completely fund development of new reusable systems. In addition, the new commercial space markets are too immature and uncertain to motivate the launch industry to undertake a project of this magnitude and risk. Low-cost launch vehicles will not be developed without a mature market to service; however, launch prices must be reduced in order for a commercial launch market to mature. This paper estimates and discusses the various benefits that may be reaped from government incentives for a commercial reusable launch vehicle program.

Space Station Environmental Control/Life Support System engineering

NASA Technical Reports Server (NTRS)

Miller, C. W.; Heppner, D. B.

1985-01-01

The present paper is concerned with a systems engineering study which has provided an understanding of the overall Space Station ECLSS (Environmental Control and Life Support System). ECLSS/functional partitioning is considered along with function criticality, technology alternatives, a technology description, single thread systems, Space Station architectures, ECLSS distribution, mechanical schematics per space station, and Space Station ECLSS characteristics. Attention is given to trade studies and system synergism. The Space Station functional description had been defined by NASA. The ECLSS will utilize technologies which embody regenerative concepts to minimize the use of expendables.

Communication analysis for the expendable explorer spacecraft

NASA Technical Reports Server (NTRS)

1990-01-01

This report provides the results of communication analysis for the baseline and enhanced performance spacecraft designs proposed for Expendable Explorer Spacecraft (EES) series of missions. Five classes of orbits (Geosynchronous, Circular-28 degree inclination, Polar-90 degree inclination, Sunsynchronous-97 degree inclination, Molniya orbit) and a set of candidate instrument payloads provided by the ESS Study Manager were used to formulate the basis for the ESS Communications Study. The study was performed to assess the feasibility of using Space Network or ground stations for supporting the communications, tracking and data handling of the candidate instruments that are proposed to be launched into the desired orbit.

The Road from the NASA Access to Space Study to a Reusable Launch Vehicle

NASA Technical Reports Server (NTRS)

Powell, Richard W.; Cook, Stephen A.; Lockwood, Mary Kae

1998-01-01

NASA is cooperating with the aerospace industry to develop a space transportation system that provides reliable access-to-space at a much lower cost than is possible with today's launch vehicles. While this quest has been on-going for many years it received a major impetus when the U.S. Congress mandated as part of the 1993 NASA appropriations bill that: "In view of budget difficulties, present and future..., the National Aeronautics and Space Administration shall ... recommend improvements in space transportation." NASA, working with other organizations, including the Department of Transportation, and the Department of Defense identified three major transportation architecture options that were to be evaluated in the areas of reliability, operability and cost. These architectural options were: (1) retain and upgrade the Space Shuttle and the current expendable launch vehicles; (2) develop new expendable launch vehicles using conventional technologies and transition to these new vehicles beginning in 2005; and (3) develop new reusable vehicles using advanced technology, and transition to these vehicles beginning in 2008. The launch needs mission model was based on 1993 projections of civil, defense, and commercial payload requirements. This "Access to Space" study concluded that the option that provided the greatest potential for meeting the cost, operability, and reliability goals was a rocket-powered single-stage-to-orbit fully reusable launch vehicle (RLV) fleet designed with advanced technologies.

Expendable launch vehicle transportation for the Space Station

NASA Technical Reports Server (NTRS)

Corban, Robert R.

1988-01-01

ELVs are presently evaluated as major components of the NASA Space Station's logistics transportation system, augmenting the cargo capacity of the Space Shuttle in support of Station productivity and operational flexibility. The ELVs in question are the Delta II, Atlas II, Titan III, Titan IV, Shuttle-C (unmanned cargo development), European Ariane 5, and Japanese H-II, as well as smaller launch vehicles and OTVs. Early definition of ELV program impacts will preclude the potentially excessive costs of future Space Station modifications.

Evolved Expendable Launch Vehicle: The Air Force Needs to Adopt an Incremental Approach to Future Acquisition Planning to Enable Incorporation of Lessons Learned

DTIC Science & Technology

2015-08-01

expressed interest in competing for national security launches, including ULA, Space Exploration Technologies, Inc. ( SpaceX ), and Orbital Sciences...launch offices, and launch service providers including ULA, SpaceX , and Orbital Sciences Corporation. We also reviewed past GAO reports on EELV...launch until 2019 at the earliest, and will still have to become certified. SpaceX earned certification for its Falcon 9 launch vehicle in May 2015, but

Space Transportation Infrastructure Supported By Propellant Depots

NASA Technical Reports Server (NTRS)

Smitherman, David; Woodcock, Gordon

2012-01-01

A space transportation infrastructure is described that utilizes propellant depot servicing platforms to support all foreseeable missions in the Earth-Moon vicinity and deep space out to Mars. The infrastructure utilizes current expendable launch vehicle (ELV) systems such as the Delta IV Heavy, Atlas V, and Falcon 9, for all crew, cargo, and propellant launches to orbit. Propellant launches are made to Low-Earth-Orbit (LEO) Depot and an Earth-Moon Lagrange Point 1 (L1) Depot to support a new reusable in-space transportation vehicles. The LEO Depot supports missions to Geosynchronous Earth Orbit (GEO) for satellite servicing and to L1 for L1 Depot missions. The L1 Depot supports Lunar, Earth-Sun L2 (ESL2), Asteroid and Mars Missions. New vehicle design concepts are presented that can be launched on current 5 meter diameter ELV systems. These new reusable vehicle concepts include a Crew Transfer Vehicle (CTV) for crew transportation between the LEO Depot, L1 Depot and missions beyond L1; a new reusable lunar lander for crew transportation between the L1 Depot and the lunar surface; and Mars orbital Depot are based on International Space Station (ISS) heritage hardware. Data provided includes the number of launches required for each mission utilizing current ELV systems (Delta IV Heavy or equivalent) and the approximate vehicle masses and propellant requirements. Also included is a discussion on affordability with ideas on technologies that could reduce the number of launches required and thoughts on how this infrastructure include competitive bidding for ELV flights and propellant services, developments of new reusable in-space vehicles and development of a multiuse infrastructure that can support many government and commercial missions simultaneously.

Economic benefits of commercial space activities

NASA Technical Reports Server (NTRS)

Stone, Barbara A.

1988-01-01

This paper discusses the current and potential impact on the economy of selected private sector space activities including materials processing in space and satellite communications. Spacehab, a commercially developed and manufactured pressurized metal cylinder which fits in the Shuttle payload bay and connects to the crew compartment is examined along with potential uses of the Shuttle external tank. Private sector upper stage development, the privatization of expendable launch vehicles, and the transfer of NASA technology are discussed.

48 CFR 1852.228-78 - Cross-waiver of liability for NASA expendable launch vehicle launches.

Code of Federal Regulations, 2010 CFR

2010-10-01

... on return from space to develop further a payload's product or process except when such development..., simulation, or guidance and control equipment and related facilities or services. (6) Related entity means...

Navigation, Guidance and Control For the CICADA Expendable Micro Air Vehicle

DTIC Science & Technology

2015-01-01

aircraft, as shown in Figure 5a. A Tempest UAV mothership was used as the host platform for the CICADA vehicles. Figure 5b shows how two CICADAs were...mounted on wing pylon drop mechanisms located on each wing of the Tempest . The Tempest was needed to carry the CICADAs back within range of the recovery...carried the Tempest and CICADA combination to a maximum altitude of 57,000 feet above sea-level. At that point, Tempest was released from the balloon and

KSC-02pd1579

NASA Image and Video Library

2002-10-18

KENNEDY SPACE CENTER, FLA. - The TDRS-J spacecraft, enclosed in a container, arrives at the Spacecraft Assembly and Encapsulation Facility-2 (SAEF-2) for processing. The Tracking and Data Relay Satellite System is the primary source of space-to-ground voice, data and telemetry for the Space Shuttle. It also provides communications with the International Space Station and scientific spacecraft in low-earth orbit such as the Hubble Space Telescope, and launch support for some expendable vehicles. This new advanced series of satellites will extend the availability of TDRS communications services until approximately 2017.

Shuttle Propulsion Overview - The Design Challenges

NASA Technical Reports Server (NTRS)

Owen, James W.

2011-01-01

The major elements of the Space Shuttle Main Propulsion System include two reusable solid rocket motors integrated into recoverable solid rocket boosters, an expendable external fuel and oxidizer tank, and three reusable Space Shuttle Main Engines. Both the solid rocket motors and space shuttle main engines ignite prior to liftoff, with the solid rocket boosters separating about two minutes into flight. The external tank separates, about eight and a half minutes into the flight, after main engine shutdown and is safely expended in the ocean. The SSME's, integrated into the Space Shuttle Orbiter aft structure, are reused after post landing inspections. The configuration is called a stage and a half as all the propulsion elements are active during the boost phase, with only the SSME s continuing operation to achieve orbital velocity. Design and performance challenges were numerous, beginning with development work in the 1970's. The solid rocket motors were large, and this technology had never been used for human space flight. The SSME s were both reusable and very high performance staged combustion cycle engines, also unique to the Space Shuttle. The multi body side mount configuration was unique and posed numerous integration and interface challenges across the elements. Operation of the system was complex and time consuming. This paper describes the design challenges and key areas where the design evolved during the program.

Small Space Launch: Origins & Challenges

NASA Astrophysics Data System (ADS)

Freeman, T.; Delarosa, J.

2010-09-01

The United States Space Situational Awareness capability continues to be a key element in obtaining and maintaining the high ground in space. Space Situational Awareness satellites are critical enablers for integrated air, ground and sea operations, and play an essential role in fighting and winning conflicts. The United States leads the world space community in spacecraft payload systems from the component level into spacecraft, and in the development of constellations of spacecraft. In the area of launch systems that support Space Situational Awareness, despite the recent development of small launch vehicles, the United States launch capability is dominated by an old, unresponsive and relatively expensive set of launchers in the Expandable, Expendable Launch Vehicles (EELV) platforms; Delta IV and Atlas V. The United States directed Air Force Space Command to develop the capability for operationally responsive access to space and use of space to support national security, including the ability to provide critical space capabilities in the event of a failure of launch or on-orbit capabilities. On 1 Aug 06, Air Force Space Command activated the Space Development & Test Wing (SDTW) to perform development, test and evaluation of Air Force space systems and to execute advanced space deployment and demonstration projects to exploit new concepts and technologies, and rapidly migrate capabilities to the warfighter. The SDTW charged the Launch Test Squadron (LTS) with the mission to develop the capability of small space launch, supporting government research and development space launches and missile defense target missions, with operationally responsive spacelift for Low-Earth-Orbit Space Situational Awareness assets as a future mission. This new mission created new challenges for LTS. The LTS mission tenets of developing space launches and missile defense target vehicles were an evolution from the squadrons previous mission of providing sounding rockets under the Rocket Sounding Launch Program (RSLP). The new mission tenets include shortened operational response periods criteria for the warfighter, while reducing the life-cycle development, production and launch costs of space launch systems. This presentation will focus on the technical challenges in transforming and integrating space launch vehicles and space craft vehicles for small space launch missions.

Communications satellite systems operations with the space station. Volume 3: Supplementary technical report

NASA Technical Reports Server (NTRS)

Price, K. M.; Russell, P.; Weyandt, C.

1988-01-01

The NASA space station has the potential to provide significant economic benefits to commercial communications satellite operators. The initial reports qunatified the benefits of space-based activities and assessed the impacts on the satellite design and the space station. Results are given for the following additional tasks: quantify the value of satellite retrievability operations and define its operational aspects; evaluate the use of expendable launch vehicles for transportation of satellites from the Earth to the space station; and quantify the economic value of modular satellites that are assembled and serviced in space.

NASA Headquarters/Kennedy Space Center: Organization and Small Spacecraft Launch Services

NASA Technical Reports Server (NTRS)

Sierra, Albert; Beddel, Darren

1999-01-01

The objectives of the Kennedy Space Center's (KSC) Expendable Launch Vehicles (ELV) Program are to provide safe, reliable, cost effective ELV launches, maximize customer satisfaction, and perform advanced payload processing capability development. Details are given on the ELV program organization, products and services, foreign launch vehicle policy, how to get a NASA launch service, and some of the recent NASA payloads.

Aeronautics and Space Report of the President: Fiscal Year 1996 Activities

NASA Technical Reports Server (NTRS)

1996-01-01

Topics considered include: (1) Space launch activities: space shuttle missions; expendable launch vehicles. (2) Space science: astronomy and space physics; solar system exploration. (3) Space flight and technology: life and microgravity sciences; space shuttle technology; reuseable launch vehicles; international space station; energy; safety and mission assurance; commercial development and regulation of space; surveillance. (4) Space communications: communications satellites; space network; ground networks; mission control and data systems. (5) Aeronautical activities: technology developments; air traffic control and navigation; weather-related aeronautical activities; flight safety and security; aviation medicine and human factors. (6) Studies of the planet earth: terrestrial studies and applications: atmospheric studies: oceanographic studies; international aeronautical and space activities; and appendices.

Space Tethers Design Criteria

NASA Technical Reports Server (NTRS)

Tomlin, Donald D.; Faile, Gwyn C.; Hayashida, Kazuo B.; Frost, Cynthia L.; Wagner, Carole Y.; Mitchell, Michael L.; Vaughn, Jason A.; Galuska, Michael J.

1998-01-01

The small expendable deployable system and tether satellite system programs did not have a uniform written criteria for tethers. The JSC safety panel asked what criteria was used to design the tethers. Since none existed, a criteria was written based on past experience for future tether programs.

Assessment of candidate-expendable launch vehicles for large payloads

NASA Technical Reports Server (NTRS)

1984-01-01

In recent years the U.S. Air Force and NASA conducted design studies of 3 expendable launch vehicle configurations that could serve as a backup to the space shuttle--the Titan 34D7/Centaur, the Atlas II/Centaur, and the shuttle-derived SRB-X--as well as studies of advanced shuttle-derived launch vehicles with much larger payload capabilities than the shuttle. The 3 candidate complementary launch vehicles are judged to be roughly equivalent in cost, development time, reliability, and payload-to-orbit performance. Advanced shuttle-derived vehicles are considered viable candidates to meet future heavy lift launch requirements; however, they do not appear likely to result in significant reduction in cost-per-pound to orbit.

Flame resistant fibrous structures development

NASA Technical Reports Server (NTRS)

Coskren, Robert J.

1992-01-01

The purpose of the current program was (1) to investigate potentially useful new polymers, both for fire safety and mechanical properties, (2) to produce fibers from these polymers if necessary, and (3) to produce sufficient quantities of qualified fibrous structures, composites, or laminates for use in various areas of the Space Shuttle and Space Station Programs. During the past six years, development efforts have been expended in several major areas in support of Space Shuttle missions and Space Station Freedom projects. The summarized results of several of these major efforts are included in this report.

The Living With a Star Space Environment Testbed Experiments

NASA Technical Reports Server (NTRS)

Xapsos, Michael A.

2014-01-01

The focus of the Living With a Star (LWS) Space Environment Testbed (SET) program is to improve the performance of hardware in the space radiation environment. The program has developed a payload for the Air Force Research Laboratory (AFRL) Demonstration and Science Experiments (DSX) spacecraft that is scheduled for launch in August 2015 on the SpaceX Falcon Heavy rocket. The primary structure of DSX is an Evolved Expendable Launch Vehicle (EELV) Secondary Payload Adapter (ESPA) ring. DSX will be in a Medium Earth Orbit (MEO). This oral presentation will describe the SET payload.

Space transportation booster engine configuration study. Volume 1: Executive Summary

NASA Technical Reports Server (NTRS)

1989-01-01

The objective of the Space Transportation Booster Engine (STBE) Configuration Study is to contribute to the Advanced Launch System (ALS) development effort by providing highly reliable, low cost booster engine concepts for both expendable and reusable rocket engines. The objectives of the Space Transportation Booster Engine (STBE) Configuration Study were to identify engine configurations which enhance vehicle performance and provide operational flexibility at low cost, and to explore innovative approaches to the follow-on full-scale development (FSD) phase for the STBE.

Space tug economic analysis study. Volume 2: Tug concepts analysis. Appendix: Tug design and performance data base

NASA Technical Reports Server (NTRS)

1972-01-01

The tug design and performance data base for the economic analysis of space tug operation are presented. A compendium of the detailed design and performance information from the data base is developed. The design data are parametric across a range of reusable space tug sizes. The performance curves are generated for selected point designs of expendable orbit injection stages and reusable tugs. Data are presented in the form of graphs for various modes of operation.

Functional requirements for onboard management of space shuttle consumables, volume 2.

NASA Technical Reports Server (NTRS)

Graf, P. J.; Herwig, H. A.; Neel, L. W.

1973-01-01

A study was conducted to develop the functional requirements for onboard management of space shuttle consumables. A specific consumables management concept for the space shuttle vehicle was developed and the functional requirements for the onboard portion of the concept were generated. Consumables management is the process of controlling or influencing the usage of expendable materials involved in vehicle subsystem operation. The subsystems considered in the study are: (1) propulsion, (2) power generation, and (3) environmental and life support.

Payload Performance Analysis for a Reusable Two-Stage-to-Orbit Vehicle

NASA Technical Reports Server (NTRS)

Tartabini, Paul V.; Beaty, James R.; Lepsch, Roger A.; Gilbert, Michael G.

2015-01-01

This paper investigates a unique approach in the development of a reusable launch vehicle where, instead of designing the vehicle to be reusable from its inception, as was done for the Space Shuttle, an expendable two stage launch vehicle is evolved over time into a reusable launch vehicle. To accomplish this objective, each stage is made reusable by adding the systems necessary to perform functions such as thermal protection and landing, without significantly altering the primary subsystems and outer mold line of the original expendable vehicle. In addition, some of the propellant normally used for ascent is used instead for additional propulsive maneuvers after staging in order to return both stages to the launch site, keep loads within acceptable limits and perform a soft landing. This paper presents a performance analysis that was performed to investigate the feasibility of this approach by quantifying the reduction in payload capability of the original expendable launch vehicle after accounting for the mass additions, trajectory changes and increased propellant requirements necessary for reusability. Results show that it is feasible to return both stages to the launch site with a positive payload capability equal to approximately 50 percent of an equivalent expendable launch vehicle. Further discussion examines the ability to return a crew/cargo capsule to the launch site and presents technical challenges that would have to be overcome.

KSC-02pd1578

NASA Image and Video Library

2002-10-18

KENNEDY SPACE CENTER, FLA. - The TDRS-J spacecraft, enclosed in a container, is transported past the Vehicle Assembly Building on its way to the Spacecraft Assembly and Encapsulation Facility-2 (SAEF-2) for processing. The Tracking and Data Relay Satellite System is the primary source of space-to-ground voice, data and telemetry for the Space Shuttle. It also provides communications with the International Space Station and scientific spacecraft in low-earth orbit such as the Hubble Space Telescope, and launch support for some expendable vehicles. This new advanced series of satellites will extend the availability of TDRS communications services until approximately 2017.

Methodology for Assessing Reusability of Spaceflight Hardware

NASA Technical Reports Server (NTRS)

Childress-Thompson, Rhonda; Thomas, L. Dale; Farrington, Phillip

2017-01-01

In 2011 the Space Shuttle, the only Reusable Launch Vehicle (RLV) in the world, returned to earth for the final time. Upon retirement of the Space Shuttle, the United States (U.S.) no longer possessed a reusable vehicle or the capability to send American astronauts to space. With the National Aeronautics and Space Administration (NASA) out of the RLV business and now only pursuing Expendable Launch Vehicles (ELV), not only did companies within the U.S. start to actively pursue the development of either RLVs or reusable components, but entities around the world began to venture into the reusable market. For example, SpaceX and Blue Origin are developing reusable vehicles and engines. The Indian Space Research Organization is developing a reusable space plane and Airbus is exploring the possibility of reusing its first stage engines and avionics housed in the flyback propulsion unit referred to as the Advanced Expendable Launcher with Innovative engine Economy (Adeline). Even United Launch Alliance (ULA) has announced plans for eventually replacing the Atlas and Delta expendable rockets with a family of RLVs called Vulcan. Reuse can be categorized as either fully reusable, the situation in which the entire vehicle is recovered, or partially reusable such as the National Space Transportation System (NSTS) where only the Space Shuttle, Space Shuttle Main Engines (SSME), and Solid Rocket Boosters (SRB) are reused. With this influx of renewed interest in reusability for space applications, it is imperative that a systematic approach be developed for assessing the reusability of spaceflight hardware. The partially reusable NSTS offered many opportunities to glean lessons learned; however, when it came to efficient operability for reuse the Space Shuttle and its associated hardware fell short primarily because of its two to four-month turnaround time. Although there have been several attempts at designing RLVs in the past with the X-33, Venture Star and Delta Clipper Experimental (DC-X), reusability within the spaceflight arena is still in its infancy. With unlimited resources (namely, time and money), almost any launch vehicle and its associated hardware can be made reusable. However, an endless supply of funds for space exploration is not the case in today's economy for neither government agencies nor their commercial counterparts. Therefore, any organization wanting to be a leader in space exploration and remain competitive in this unforgiving space faring industry must confront shrinking budgets with more cost conscious and efficient designs. Therefore, standards for developing reusable spaceflight hardware need to be established. By having standards available to existing and emerging companies, some of the potential roadblocks and limitations that plagued previous attempts at reuse may be minimized or completely avoided.

Advanced extravehicular protective systems study, volume 1

NASA Technical Reports Server (NTRS)

Sutton, J. G.; Heimlich, P. F.; Tepper, E. H.

1972-01-01

An appraisal was made of advanced portable and emergency life support systems concepts for space station, space shuttle, lunar base, and Mars EVA missions. Specifications are given, and the methodology is described. Subsystem studies and systems integration efforts are summarized. Among the conclusions are the following: (1) For long duration missions, a configuration incorporating a regenerable CO2 control subsystem and a thermal control subsystem utilizing a minimum of expendables decreases the vehicle penalty of present configurations. (2) For shorter duration missions, a configuration incorporating an expendable water thermal control subsystem is the most competitive subsystem; regenerable CO2 control subsystems if properly developed are competitive with nonregenerable counterparts. (3) The CO2 reduction and oxygen reclamation withing the parent vehicle is only competitive when there are three or more parent vehicle resupply periods. (4) For long duration emergency systems of one hour or more, inherent redundancy within the primary configuration to provide emergency thermal control is the most competitive approach.

Artificial intelligent decision support for low-cost launch vehicle integrated mission operations

NASA Astrophysics Data System (ADS)

Szatkowski, Gerard P.; Schultz, Roger

1988-11-01

The feasibility, benefits, and risks associated with Artificial Intelligence (AI) Expert Systems applied to low cost space expendable launch vehicle systems are reviewed. This study is in support of the joint USAF/NASA effort to define the next generation of a heavy-lift Advanced Launch System (ALS) which will provide economical and routine access to space. The significant technical goals of the ALS program include: a 10 fold reduction in cost per pound to orbit, launch processing in under 3 weeks, and higher reliability and safety standards than current expendables. Knowledge-based system techniques are being explored for the purpose of automating decision support processes in onboard and ground systems for pre-launch checkout and in-flight operations. Issues such as: satisfying real-time requirements, providing safety validation, hardware and Data Base Management System (DBMS) interfacing, system synergistic effects, human interfaces, and ease of maintainability, have an effect on the viability of expert systems as a useful tool.

Artificial intelligent decision support for low-cost launch vehicle integrated mission operations

NASA Technical Reports Server (NTRS)

Szatkowski, Gerard P.; Schultz, Roger

1988-01-01

The feasibility, benefits, and risks associated with Artificial Intelligence (AI) Expert Systems applied to low cost space expendable launch vehicle systems are reviewed. This study is in support of the joint USAF/NASA effort to define the next generation of a heavy-lift Advanced Launch System (ALS) which will provide economical and routine access to space. The significant technical goals of the ALS program include: a 10 fold reduction in cost per pound to orbit, launch processing in under 3 weeks, and higher reliability and safety standards than current expendables. Knowledge-based system techniques are being explored for the purpose of automating decision support processes in onboard and ground systems for pre-launch checkout and in-flight operations. Issues such as: satisfying real-time requirements, providing safety validation, hardware and Data Base Management System (DBMS) interfacing, system synergistic effects, human interfaces, and ease of maintainability, have an effect on the viability of expert systems as a useful tool.

Turnaround Operations Analysis for OTV. Volume 3: Technology Development Plan

NASA Technical Reports Server (NTRS)

1988-01-01

An integrated technology development plan for the technologies required to process both GBOTVs and SBOTVs are described. The plan includes definition of the tests and experiments to be accomplished on the ground, in a Space Shuttle Sortie Mission, on an Expendable Launch Vehicle, or at the Space Station as a Technology Development Mission (TDM). The plan reflects and accommodates current and projected research and technology programs where appropriate.

Shuttle user analysis (study 2.2). Volume 3: Business risk and value of operations in space (BRAVO). Part 5: Analysis of GSFC Earth Observation Satellite (EOS) system mission model using BRAVO techniques

NASA Technical Reports Server (NTRS)

1975-01-01

Cost comparisons were made between three modes of operation (expend, ground refurbish, and space resupply) for the Earth Observation System (EOS-B) to furnish data to NASA on alternative ways to use the shuttle/EOS. Results of the analysis are presented in tabular form.

KSC-03pd0023

NASA Image and Video Library

2003-01-05

KENNEDY SPACE CENTER, FLA. -- In the Multi-Purpose Processing Facility, a technician cleans NASA's Solar Radiation and Climate Experiment (SORCE) before its mating to the Pegasus XL Expendable Launch Vehicle. Built by Orbital Sciences Space Systems Group, SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere. The launch of SORCE is scheduled for Jan. 25 at 3:14 p.m. from Cape Canaveral Air Force Station, Fla.

Reusability aspects for space transportation rocket engines: programmatic status and outlook

NASA Astrophysics Data System (ADS)

Preclik, D.; Strunz, R.; Hagemann, G.; Langel, G.

2011-09-01

Rocket propulsion systems belong to the most critical subsystems of a space launch vehicle, being illustrated in this paper by comparing different types of transportation systems. The aspect of reusability is firstly discussed for the space shuttle main engine, the only rocket engine in the world that has demonstrated multiple reuses. Initial projections are contrasted against final reusability achievements summarizing three decades of operating the space shuttle main engine. The discussion is then extended to engines employed on expendable launch vehicles with an operational life requirement typically specifying structural integrities up to 20 cycles (start-ups) and an accumulated burning time of about 6,000 s (Vulcain engine family). Today, this life potential substantially exceeds the duty cycle of an expendable engine. It is actually exploited only during the development and qualification phase of an engine when system reliability is demonstrated on ground test facilities with a reduced number of hardware sets that are subjected to an extended number of test cycles and operation time. The paper will finally evaluate the logic and effort necessary to qualify a reusable engine for a required reliability and put this result in context of possible cost savings realized from reuse operations over a time span of 25 years.

EELV Secondary Payload Adapter (ESPA)

NASA Astrophysics Data System (ADS)

Haskett, Scott A.; Weis, Steven C.; Doggrell, Leslie J.; Sciulli, Dino; Meink, Troy E.; Ganley, Jeff T.; Maly, Joseph R.; Jurisson, Karl

2000-11-01

Despite growing international interest in small satellites, high dedicated expendable launch vehicle costs and the lack of secondary launch opportunities continue to hinder the full exploitation of small satellite technology. In the United States, the Department of Defense (DoD), NASA, other government agencies, commercial companies, and many universities use small satellites to perform space experiments, demonstrate new technology, and test operational prototype hardware. In addition, the DoD continues to study the role of small satellites in fulfilling operational mission requirements. However, the US lacks sufficient small satellite launch capacity. Furthermore, US government agencies are restricted to the use of US launch vehicles, which eliminates many affordable launch opportunities. In an effort to increase the number of space experiments that can be flown with a small, fixed budget, the DoD Space Test Program (STP) has teamed with the Air Force Research Laboratory Space Vehicles Directorate (AFRL/VS) to develop a low-cost solution for the small satellite launch program. Our solution, which can be implemented on both Boeing and Lockheed-Martin Evolved Expendable Launch Vehicle-Medium (EELV-M) boosters, is called the EELV Secondary Payload Adaptor (ESPA). ESPA will increase the number of launch opportunities for 180kg-class (or smaller) satellites at prices highly competitive with other secondary launch services worldwide.

Space Transportation Infrastructure Supported By Propellant Depots

NASA Technical Reports Server (NTRS)

Smitherman, David; Woodcock, Gordon

2011-01-01

A space transportation infrastructure is described that utilizes propellant depots to support all foreseeable missions in the Earth-Moon vicinity and deep space out to Mars. The infrastructure utilizes current expendable launch vehicles such as the Delta IV Heavy, Atlas V, and Falcon 9, for all crew, cargo, and propellant launches to orbit. Propellant launches are made to a Low-Earth-Orbit (LEO) Depot and an Earth-Moon Lagrange Point 1 (L1) Depot to support new reusable in-space transportation vehicles. The LEO Depot supports missions to Geosynchronous Earth Orbit (GEO) for satellite servicing, and to L1 for L1 Depot missions. The L1 Depot supports Lunar, Earth-Sun L2 (ESL2), Asteroid, and Mars missions. A Mars Orbital Depot is also described to support ongoing Mars missions. New concepts for vehicle designs are presented that can be launched on current 5-meter diameter expendable launch vehicles. These new reusable vehicle concepts include a LEO Depot, L1 Depot, and Mars Orbital Depot based on International Space Station (ISS) heritage hardware. The high-energy depots at L1 and Mars orbit are compatible with, but do not require, electric propulsion tug use for propellant and/or cargo delivery. New reusable in-space crew transportation vehicles include a Crew Transfer Vehicle (CTV) for crew transportation between the LEO Depot and the L1 Depot, a new reusable Lunar Lander for crew transportation between the L1 Depot and the lunar surface, and a Deep Space Habitat (DSH) to support crew missions from the L1 Depot to ESL2, Asteroid, and Mars destinations. A 6 meter diameter Mars lander concept is presented that can be launched without a fairing based on the Delta IV heavy Payload Planners Guide, which indicates feasibility of a 6.5 meter fairing. This lander would evolve to re-usable operations when propellant production is established on Mars. Figure 1 provides a summary of the possible missions this infrastructure can support. Summary mission profiles are presented for each primary mission capability. These profiles are the basis for propellant loads, numbers of vehicles/stages and launches for each mission capability. Data includes the number of launches required for each mission utilizing current expendable launch vehicle systems, and concluding remarks include ideas for reducing the number of launches through incorporation of heavy-lift launch vehicles, solar electric propulsion, and other transportation support concepts.

Loosely Coupled GPS-Aided Inertial Navigation System for Range Safety

NASA Technical Reports Server (NTRS)

Heatwole, Scott; Lanzi, Raymond J.

2010-01-01

The Autonomous Flight Safety System (AFSS) aims to replace the human element of range safety operations, as well as reduce reliance on expensive, downrange assets for launches of expendable launch vehicles (ELVs). The system consists of multiple navigation sensors and flight computers that provide a highly reliable platform. It is designed to ensure that single-event failures in a flight computer or sensor will not bring down the whole system. The flight computer uses a rules-based structure derived from range safety requirements to make decisions whether or not to destroy the rocket.

Thermal Orbital Environmental Parameter Study on the Propulsive Small Expendable Deployer System (ProSEDS) Using Earth Radiation Budget Experiment (ERBE) Data

NASA Technical Reports Server (NTRS)

Sharp, John R.; McConnaughey, Paul K. (Technical Monitor)

2002-01-01

The natural thermal environmental parameters used on the Space Station Program (SSP 30425) were generated by the Space Environmental Effects Branch at NASA's Marshall Space Flight Center (MSFC) utilizing extensive data from the Earth Radiation Budget Experiment (ERBE), a series of satellites which measured low earth orbit (LEO) albedo and outgoing long-wave radiation. Later, this temporal data was presented as a function of averaging times and orbital inclination for use by thermal engineers in NASA Technical Memorandum TM 4527. The data was not presented in a fashion readily usable by thermal engineering modeling tools and required knowledge of the thermal time constants and infrared versus solar spectrum sensitivity of the hardware being analyzed to be used properly. Another TM was recently issued as a guideline for utilizing these environments (NASA/TM-2001-211221) with more insight into the utilization by thermal analysts. This paper gives a top-level overview of the environmental parameters presented in the TM and a study of the effects of implementing these environments on an ongoing MSFC project, the Propulsive Small Expendable Deployer System (ProSEDS), compared to conventional orbital parameters that had been historically used.

Buying a Shuttle ticket

NASA Technical Reports Server (NTRS)

Moore, W. F.; Forsythe, C.

1977-01-01

A preliminary draft policy for reimbursement for Space Shuttle flights has been developed by NASA in the form of pricing criteria for Space Transportation System (STS) users in domestic and foreign government and industry. The reimbursement policy, the transition from expendable launch vehicles to STS, the new user services, and the interaction of the economics of new user services and STS cost to fly are discussed in the present paper. Current efforts to develop new users are noted.

Early Program Development

NASA Image and Video Library

1970-01-01

In 1970, NASA initiated Phase A contracts to study alternate Space Shuttle designs in addition to the two-stage fully-reusable Space Shuttle system already under development. A number of alternate systems were developed to ensure the development of the optimum earth-to-orbit system, including the Stage-and-a-half Chemical Interorbital Shuttle, shown here. The concept would utilize a reusable marned spacecraft with an onboard propulsion system attached to an expendable fuel tank to provide supplementary propellants.

KSC-03pd0021

NASA Image and Video Library

2003-01-05

KENNEDY SPACE CENTER, FLA. -- The Pegasus XL Expendable Launch Vehicle is on a workstand in the Multi-Purpose Processing Facility. The Pegasus XL will carry NASA's Solar Radiation and Climate Experiment (SORCE) into orbit. Built by Orbital Sciences Space Systems Group, SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere. The launch of SORCE is scheduled for Jan. 25 at 3:14 p.m. from Cape Canaveral Air Force Station, Fla.

KSC-03pd0022

NASA Image and Video Library

2003-01-05

KENNEDY SPACE CENTER, FLA. -- The Pegasus XL Expendable Launch Vehicle is on a workstand in the Multi-Purpose Processing Facility. The Pegasus XL will carry NASA's Solar Radiation and Climate Experiment (SORCE) into orbit. Built by Orbital Sciences Space Systems Group, SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere. The launch of SORCE is scheduled for Jan. 25 at 3:14 p.m. from Cape Canaveral Air Force Station, Fla.

Overview of rocket engine control

NASA Technical Reports Server (NTRS)

Lorenzo, Carl F.; Musgrave, Jeffrey L.

1991-01-01

The issues of Chemical Rocket Engine Control are broadly covered. The basic feedback information and control variables used in expendable and reusable rocket engines, such as Space Shuttle Main Engine, are discussed. The deficiencies of current approaches are considered and a brief introduction to Intelligent Control Systems for rocket engines (and vehicles) is presented.

Payload design requirements analysis (study 2.2). Volume 3. Guideline analysis. [economic analysis of payloads for space shuttles and space tugs

NASA Technical Reports Server (NTRS)

Shiokari, T.

1973-01-01

Payloads to be launched on the space shuttle/space tug/sortie lab combinations are discussed. The payloads are of four types: (1) expendable, (2) ground refurbishable, (3) on-orbit maintainable, and (4) sortie. Economic comparisons are limited to the four types of payloads described. Additional system guidelines were developed by analyzing two payloads parameterically and demonstrating the results on an example satellite. In addition to analyzing the selected guidelines, emphasis was placed on providing economic tradeoff data and identifying payload parameters influencing the low cost approaches.

Aeronautics and space report of the President, 1983 activities

NASA Technical Reports Server (NTRS)

1984-01-01

Achievements in communication; space science; space transportation; aeronautics; and Earth resources and environment are summarized. Activities of the various Federal agencies and cooperation with NASA in these areas are described. The Presidential policy announcement on the endorsement of commercial operation of expendable launch vehicles is included. Tables show, the space activities budget; a historical budget summary, U.S. space launch vehicles; U.S. and Soviet manned spaceflights, 1961 to 1983; U.S. launched space probes, 1975 to 1983; U.S. launched scientific and applications satellites, 1978 to 1983; the U.S. spacecraft record; the world record of space launches successful in attaining Earth orbit or beyond; and successful U.S. launchings for 1983.

Ground Robotic Hand Applications for the Space Program study (GRASP)

NASA Astrophysics Data System (ADS)

Grissom, William A.; Rafla, Nader I.

1992-04-01

This document reports on a NASA-STDP effort to address research interests of the NASA Kennedy Space Center (KSC) through a study entitled, Ground Robotic-Hand Applications for the Space Program (GRASP). The primary objective of the GRASP study was to identify beneficial applications of specialized end-effectors and robotic hand devices for automating any ground operations which are performed at the Kennedy Space Center. Thus, operations for expendable vehicles, the Space Shuttle and its components, and all payloads were included in the study. Typical benefits of automating operations, or augmenting human operators performing physical tasks, include: reduced costs; enhanced safety and reliability; and reduced processing turnaround time.

Economics in ground operations of the Space Shuttle

NASA Technical Reports Server (NTRS)

Gray, R. H.

1973-01-01

The physical configuration, task versatility, and typical mission profile of the Space Shuttle are illustrated and described, and a comparison of shuttle and expendable rocket costs is discussed, with special emphasis upon savings to be achieved in ground operations. A review of economies achieved by engineering design improvements covers the automated checkout by onboard shuttle systems, the automated launch processing system, the new maintenance concept, and the analogy of Space Shuttle and airline repetitive operations. The Space Shuttle is shown to represent a new level in space flight technology, particularly, the sophistication of the systems and procedures devised for its support and ground operations.

Early Program Development

NASA Image and Video Library

1996-06-20

Engineers at one of MSFC's vacuum chambers begin testing a microthruster model. The purpose of these tests are to collect sufficient data that will enabe NASA to develop microthrusters that will move the Space Shuttle, a future space station, or any other space related vehicle with the least amount of expended energy. When something is sent into outer space, the forces that try to pull it back to Earth (gravity) are very small so that it only requires a very small force to move very large objects. In space, a force equal to a paperclip can move an object as large as a car. Microthrusters are used to produce these small forces.

Commercial development of space - A national commitment

NASA Technical Reports Server (NTRS)

Rose, James T.; Stone, Barbara A.

1989-01-01

The United States is currently in a unique position. It has all the assets required to lead the world in commercial space development. It has the transportation: the Shuttle and a family of expendable launch vehicles. Space Station Freedom is forthcoming. It has the extrepreneurial spirit, coupled with a strong university system and lending institutions with financial capacity necessary for entrepreneurial activities. But, there are a number of actions that the government should take to improve the climate and prospects for greater commercial development of space. This paper outlines some of the steps that NASA is taking to incentivize the private sector to apply its resources and talents to commercial space endeavors.

Ground Robotic Hand Applications for the Space Program study (GRASP)

NASA Technical Reports Server (NTRS)

Grissom, William A.; Rafla, Nader I. (Editor)

1992-01-01

This document reports on a NASA-STDP effort to address research interests of the NASA Kennedy Space Center (KSC) through a study entitled, Ground Robotic-Hand Applications for the Space Program (GRASP). The primary objective of the GRASP study was to identify beneficial applications of specialized end-effectors and robotic hand devices for automating any ground operations which are performed at the Kennedy Space Center. Thus, operations for expendable vehicles, the Space Shuttle and its components, and all payloads were included in the study. Typical benefits of automating operations, or augmenting human operators performing physical tasks, include: reduced costs; enhanced safety and reliability; and reduced processing turnaround time.

Space Transportation Booster Engine Configuration Study. Volume 3: Program Cost estimates and work breakdown structure and WBS dictionary

NASA Technical Reports Server (NTRS)

1989-01-01

The objective of the Space Transportation Booster Engine Configuration Study is to contribute to the ALS development effort by providing highly reliable, low cost booster engine concepts for both expendable and reusable rocket engines. The objectives of the Space Transportation Booster Engine (STBE) Configuration Study were: (1) to identify engine development configurations which enhance vehicle performance and provide operational flexibility at low cost; and (2) to explore innovative approaches to the follow-on Full-Scale Development (FSD) phase for the STBE.

NASA replanning efforts continue

NASA Astrophysics Data System (ADS)

Katzoff, Judith A.

A task force of the National Aeronautics and Space Administration (NASA) is producing new launch schedules for NASA's three remaining space shuttle orbiters, possibly supplemented by expendable launch vehicles. In the wake of the explosion of the space shuttle Challenger on January 28, 1986, the task force is assuming a delay of 12-18 months before resumption of shuttle flights.NASA's Headquarters Replanning Task Force, which meets daily, is separate from the agency's Data and Design Analysis Task Force, which collects and analyzes information about the accident for the use of the investigative commission appointed by President Ronald Reagan.

Space transportation booster engine configuration study. Volume 2: Design definition document and environmental analysis

NASA Technical Reports Server (NTRS)

1989-01-01

The objective of the Space Transportation Booster Engine (STBE) Configuration Study is to contribute to the Advanced Launch System (ALS) development effort by providing highly reliable, low cost booster engine concepts for both expendable and reusable rocket engines. The objectives of the space Transportation Booster Engine (STBE) Configuration Study were: (1) to identify engine configurations which enhance vehicle performance and provide operational flexibility at low cost, and (2) to explore innovative approaches to the follow-on Full-Scale Development (FSD) phase for the STBE.

International Space Station (ISS)

NASA Image and Video Library

2000-10-29

The Soyuz TM-31 launch vehicle is shown in the vertical position for its launch from Baikonur, carrying the first resident crew to the International Space Station. The Russian Soyuz launch vehicle is an expendable spacecraft that evolved out of the original Class A (Sputnik). From the early 1960s until today, the Soyuz launch vehicle has been the backbone of Russia's marned and unmanned space launch fleet. Today, the Soyuz launch vehicle is marketed internationally by a joint Russian/French consortium called STARSEM. As of August 2001, there have been ten Soyuz missions under the STARSEM banner.

International Space Station (ISS)

NASA Image and Video Library

2000-10-29

The Soyuz TM-31 launch vehicle, which carried the first resident crew to the International Space Station, moves toward the launch pad at the Baikonur complex in Kazakhstan. The Russian Soyuz launch vehicle is an expendable spacecraft that evolved out of the original Class A (Sputnik). From the early 1960' until today, the Soyuz launch vehicle has been the backbone of Russia's marned and unmanned space launch fleet. Today, the Soyuz launch vehicle is marketed internationally by a joint Russian/French consortium called STARSEM. As of August 2001, there have been ten Soyuz missions under the STARSEM banner.

Design and Testing of a One-Third Scale Soyuz TM Descent Module Spartan Conversion Project Super Loki Instrumentation

NASA Technical Reports Server (NTRS)

Anderson, Loren A.; Armitage, Pamela Kay

1993-01-01

The 1992-1993 senior Aerospace Engineering Design class continued work on the post landing configurations for the Assured Crew Return Vehicle. The Assured Crew Return Vehicle will be permanently docked to the space station fulfilling NASA's commitment of Assured Crew Return Capability in the event of an accident or illness aboard the space station. The objective of the project was to give the Assured Crew Return Vehicle Project Office data to feed into their feasibility studies. Three design teams were given the task of developing models with dynamically and geometrically scaled characteristics. Groups one and two combined efforts to design a one-third scale model of the Russian Soyuz TM Descent Module, and an on-board flotation system. This model was designed to determine the flotation characteristics and test the effects of a rigid flotation and orientation system. Group three designed a portable water wave test facility to be located on campus. Because of additional funding from Thiokol Corporation, testing of the Soyuz model and flotation systems took place at the Offshore Technology Research Center. Universities Space Research Association has been studying the use of small expendable launch vehicles for missions which cost less than 200 million dollars. The Crusader2B. which consists of the original Spartan first and second stage with an additional Spartan second stage and the Minuteman III upper stage is being considered for this task. University of Central Florida project accomplishments include an analysis of launch techniques, a modeling technique to determine flight characteristics, and input into the redesign of an existing mobile rail launch platform.

Aeronautics and Space Report of the President

NASA Technical Reports Server (NTRS)

1991-01-01

The years 1989 to 1990 activities are reported including human space flight, unmanned expendable launch vehicles, space science and applications, space communications operations, space research and technology, and aeronautics research and technology. Contributions made by the 14 participating government organizations are outline. Each organization's aeronautics and/or space activities for the year are presented. The organizations involved include: (1) NASA; (2) Dept. of Defense; (3) Dept. of Commerce; (4) Dept. of Energy; (5) Dept. of the Interior; (6) Dept. of Agriculture; (7) Federal Communications Commission; (8) Dept. of Transportation; (9) Environmental Protection Agency; (10) National Science Foundation; (11) Smithsonian Institution; (12) Dept. of State; (13) Arms Control and Disarmament; and (14) United States Information Agency.

The Application of the Human Engineering Modeling and Performance Laboratory for Space Vehicle Ground Processing Tasks at Kennedy Space Center

NASA Technical Reports Server (NTRS)

Woodbury, Sarah K.

2008-01-01

The introduction of United Space Alliance's Human Engineering Modeling and Performance Laboratory began in early 2007 in an attempt to address the problematic workspace design issues that the Space Shuttle has imposed on technicians performing maintenance and inspection operations. The Space Shuttle was not expected to require the extensive maintenance it undergoes between flights. As a result, extensive, costly resources have been expended on workarounds and modifications to accommodate ground processing personnel. Consideration of basic human factors principles for design of maintenance is essential during the design phase of future space vehicles, facilities, and equipment. Simulation will be needed to test and validate designs before implementation.

The economics of satellite maintenance

NASA Technical Reports Server (NTRS)

Derocher, W. L., Jr.; Sosnay, R. G.

1975-01-01

The primary goal of the space transportation system - to reduce the cost of space programs while satisfying their mission requirements - can be enhanced by the proper choice of a satellite-maintenance concept. This paper develops the life-cycle costs of performing an automated satellite program during the shuttle era in three competitive modes: expendable, ground-refurbishable, and in-orbit maintainable. In-orbit maintenance is shown to be the most economic maintenance mode for both low- and high-earth orbits.

Earth Science

NASA Image and Video Library

1992-07-24

A Delta II rocket carrying the Geomagnetic Tail Lab (GEOTAIL) spacecraft lifts off at Launch Complex 17, Kennedy Space Center (KSC) into a cloud-dappled sky. This liftoff marks the first Delta launch under the medium expendable launch vehicle services contract between NASA and McDonnell Douglas Space Systems Co. The GEOTAIL mission, a joint US/Japanese project, is the first in a series of five satellites to study the interactions between the Sun, the Earth's magnetic field, and the Van Allen radiation belts.

Understanding Mechanical Design with Respect to Manufacturability

NASA Technical Reports Server (NTRS)

Mondell, Skyler

2010-01-01

At the NASA Prototype Development Laboratory in Kennedy Space Center, Fl, several projects concerning different areas of mechanical design were undertaken in order to better understand the relationship between mechanical design and manufacturabiIity. The assigned projects pertained specifically to the NASA Space Shuttle, Constellation, and Expendable Launch Vehicle programs. During the work term, mechanical design practices relating to manufacturing processes were learned and utilized in order to obtain an understanding of mechanical design with respect to manufacturability.

Shuttle/Agena study. Volume 2, part 1: Program requirements, conclusions, recommendations

NASA Technical Reports Server (NTRS)

1972-01-01

An evaluation to determine the compatibility of the Agena with the space transportation system for use as an expendable third stage to the space shuttle was conducted. The Agena was considered for those missions requiring additional propulsion capability beyond that used for low earth orbit. The study defines the interface requirements imposed on both the Agena and the shuttle system and identifies those areas where the Agena must be improved or modified to satisfy mission requirements.

Macroeconomic Benefits of Low-Cost Reusable Launch Vehicles

NASA Technical Reports Server (NTRS)

Shaw, Eric J.; Greenberg, Joel

1998-01-01

The National Aeronautics and Space Administration (NASA) initiated its Reusable Launch Vehicle (RLV) Technology Program to provide information on the technical and commercial feasibility of single-stage to orbit (SSTO), fully-reusable launchers. Because RLVs would not depend on expendable hardware to achieve orbit, they could take better advantage of economies of scale than expendable launch vehicles (ELVs) that discard costly hardware on ascent. The X-33 experimental vehicle, a sub-orbital, 60%-scale prototype of Lockheed Martin's VentureStar SSTO RLV concept, is being built by Skunk Works for a 1999 first flight. If RLVs achieve prices to low-earth orbit of less than $1000 US per pound, they could hold promise for eliciting an elastic response from the launch services market. As opposed to the capture of existing market, this elastic market would represent new space-based industry businesses. These new opportunities would be created from the next tier of business concepts, such as space manufacturing and satellite servicing, that cannot earn a profit at today's launch prices but could when enabled by lower launch costs. New business creation contributes benefits to the US Government (USG) and the US economy through increases in tax revenues and employment. Assumptions about the costs and revenues of these new ventures, based on existing space-based and aeronautics sector businesses, can be used to estimate the macroeconomic benefits provided by new businesses. This paper examines these benefits and the flight prices and rates that may be required to enable these new space industries.

In-Situ Resource Utilization for Space Exploration: Resource Processing, Mission-Enabling Technologies, and Lessons for Sustainability on Earth and Beyond

NASA Technical Reports Server (NTRS)

Hepp, A. F.; Palaszewski, B. A.; Landis, G. A.; Jaworske, D. A.; Colozza, A. J.; Kulis, M. J.; Heller, R. S.

2015-01-01

As humanity begins to reach out into the solar system, it has become apparent that supporting a human or robotic presence in transit andor on station requires significant expendable resources including consumables (to support people), fuel, and convenient reliable power. Transporting all necessary expendables is inefficient, inconvenient, costly, and, in the final analysis, a complicating factor for mission planners and a significant source of potential failure modes. Over the past twenty-five years, beginning with the Space Exploration Initiative, researchers at the NASA Glenn Research Center (GRC), academic collaborators, and industrial partners have analyzed, researched, and developed successful solutions for the challenges posed by surviving and even thriving in the resource limited environment(s) presented by near-Earth space and non-terrestrial surface operations. In this retrospective paper, we highlight the efforts of the co-authors in resource simulation and utilization, materials processing and consumable(s) production, power systems and analysis, fuel storage and handling, propulsion systems, and mission operations. As we move forward in our quest to explore space using a resource-optimized approach, it is worthwhile to consider lessons learned relative to efficient utilization of the (comparatively) abundant natural resources and improving the sustainability (and environment) for life on Earth. We reconsider Lunar (and briefly Martian) resource utilization for potential colonization, and discuss next steps moving away from Earth.

In-Situ Resource Utilization for Space Exploration: Resource Processing, Mission-Enabling Technologies, and Lessons for Sustainability on Earth and Beyond

NASA Technical Reports Server (NTRS)

Hepp, A. F.; Palaszewski, B. A.; Landis, G. A.; Jaworske, D. A.; Colozza, A. J.; Kulis, M. J.; Heller, Richard S.

2014-01-01

As humanity begins to reach out into the solar system, it has become apparent that supporting a human or robotic presence in transit and/or on station requires significant expendable resources including consumables (to support people), fuel, and convenient reliable power. Transporting all necessary expendables is inefficient, inconvenient, costly, and, in the final analysis, a complicating factor for mission planners and a significant source of potential failure modes. Over the past twenty-five years, beginning with the Space Exploration Initiative, researchers at the NASA Glenn Research Center (GRC), academic collaborators, and industrial partners have analyzed, researched, and developed successful solutions for the challenges posed by surviving and even thriving in the resource limited environment(s) presented by near-Earth space and non-terrestrial surface operations. In this retrospective paper, we highlight the efforts of the co-authors in resource simulation and utilization, materials processing and consumable(s) production, power systems and analysis, fuel storage and handling, propulsion systems, and mission operations. As we move forward in our quest to explore space using a resource-optimized approach, it is worthwhile to consider lessons learned relative to efficient utilization of the (comparatively) abundant natural resources and improving the sustainability (and environment) for life on Earth. We reconsider Lunar (and briefly Martian) resource utilization for potential colonization, and discuss next steps moving away from Earth.

The Application of a Residual Risk Evaluation Technique Used for Expendable Launch Vehicles

NASA Technical Reports Server (NTRS)

Latimer, John A.

2009-01-01

This presentation provides a Residual Risk Evaluation Technique (RRET) developed by Kennedy Space Center (KSC) Safety and Mission Assurance (S&MA) Launch Services Division. This technique is one of many procedures used by S&MA at KSC to evaluate residual risks for each Expendable Launch Vehicle (ELV) mission. RRET is a straight forward technique that incorporates the proven methodology of risk management, fault tree analysis, and reliability prediction. RRET derives a system reliability impact indicator from the system baseline reliability and the system residual risk reliability values. The system reliability impact indicator provides a quantitative measure of the reduction in the system baseline reliability due to the identified residual risks associated with the designated ELV mission. An example is discussed to provide insight into the application of RRET.

Use of fellowships

NASA Technical Reports Server (NTRS)

Gierasch, Peter J.

1990-01-01

The effective use of Space Grant Program fellowships are critical in meeting program objectives. In the first year of operation, the 21 colleges/consortia will expend from 30-40 percent of their grants for fellowships; program policy will allow up to 50 percent to be spent for fellowships. Thus, fellowship policy must be carefully implemented and monitored.

Propulsive Small Expendable Deployer System (ProSEDS)

NASA Technical Reports Server (NTRS)

1999-01-01

This Quick Time movie is of NASA's Propulsive Small Expendable Deployer System experiment (ProSEDS). ProSEDS will demonstrate the use of an electrodynamic tether, basically a long, thin wire, for propulsion. An electrodynamic tether uses the same principles as electric motors in toys, appliances and computer disk drives, and generators in automobiles and power plants. When electrical current is flowing through the tether, a magnetic field is produced that pushes against the magnetic field of the Earth. For ProSEDS, the current in the tether results by virtue of the voltage generated when the tether moves through the Earth's magnetic field at more than 17,000 mph. This approach can produce drag thrust generating useable power. Since electrodynamic tethers require no propellant, they could substantially reduce the weight of the spacecraft and provide a cost-effective method of reboosting spacecraft. The tether would be a 3.1-mile (5 kilometer) long, ultrathin base-wire tether connected with a 6.2-mile (10 kilometer) long nonconducting tether. The ProSEDS experiment is managed by the Space Transportation Directorate at the Marshall Space Flight Center.

The commercial implications of the EELV program

NASA Astrophysics Data System (ADS)

Sasso, Steven E.

1998-01-01

There have been several studies over the past 15 years intended to define and develop a space launch system that would meet future needs of the United States Government (USG). While these past studies (Advanced Launch System, National Launch System, Spacelifter, etc) yielded valuable data, none were carried to fruition. Overriding issues included high development cost, changing requirements, and uncertainty in the mission model, as well lack of a clear direction for where this nation should be headed. In 1995, the Air Force embarked on the Evolved Expendable Launch Vehicle (EELV) program as a way of defining and developing the next-generation expendable launch system. This time groundrules for this effort were clearly defined-the program relied on the use of evolving a system rather than developing a high-technology solution to reduce development cost, and the commercial market was factored in as a way of reducing cost to the USG. The EELV program is nearing the engineering manufacturing development (EMD) phase by mid-1998 with first flight planned for early 2001. This paper describes the planned Lockheed Martin EELV program and its ability to utilize the commercial market to benefit the USG in its need to develop the next-generation expendable launch vehicle.

NASA Tech Briefs, November 2012

NASA Technical Reports Server (NTRS)

2012-01-01

The topics include: Visual System for Browsing, Analysis, and Retrieval of Data (ViSBARD); Time-Domain Terahertz Computed Axial Tomography NDE System; Adaptive Sampling of Time Series During Remote Exploration; A Tracking Sun Photometer Without Moving Parts; Surface Temperature Data Analysis; Modular, Autonomous Command and Data Handling Software with Built-In Simulation and Test; In-Situ Wire Damage Detection System; Amplifier Module for 260-GHz Band Using Quartz Waveguide Transitions; Wideband Agile Digital Microwave Radiometer; Buckyball Nucleation of HiPco Tubes; FACT, Mega-ROSA, SOLAROSA; An Integrated, Layered-Spinel Composite Cathode for Energy Storage Applications; Engineered Multifunctional Surfaces for Fluid Handling; Polyolefin-Based Aerogels; Adjusting Permittivity by Blending Varying Ratios of SWNTs; Gravity-Assist Mechanical Simulator for Outreach; Concept for Hydrogen-Impregnated Nanofiber/Photovoltaic Cargo Stowage System; DROP: Durable Reconnaissance and Observation Platform; Developing Physiologic Models for Emergency Medical Procedures Under Microgravity; Spectroscopic Chemical Analysis Methods and Apparatus; Low Average Sidelobe Slot Array Antennas for Radiometer Applications; Motion-Corrected 3D Sonic Anemometer for Tethersondes and Other Moving Platforms; Water Treatment Systems for Long Spaceflights; Microchip Non-Aqueous Capillary Electrophoresis (MicronNACE) Method to Analyze Long-Chain Primary Amines; Low-Cost Phased Array Antenna for Sounding Rockets, Missiles, and Expendable Launch Vehicles; Mars Science Laboratory Engineering Cameras; Seismic Imager Space Telescope; Estimating Sea Surface Salinity and Wind Using Combined Passive and Active L-Band Microwave Observations; A Posteriori Study of a DNS Database Describing Super critical Binary-Species Mixing; Scalable SCPPM Decoder; QuakeSim 2.0; HURON (HUman and Robotic Optimization Network) Multi-Agent Temporal Activity Planner/Scheduler; MPST Software: MoonKommand

SCORPIUS, A New Generation of Responsive, Low Cost Expendable Launch Vehicles

NASA Astrophysics Data System (ADS)

Conger, R. E.; Chakroborty, S. P.; Wertz, J. R.

2002-01-01

The Scorpius vehicle family extends from one and two stage sub-orbital vehicles for target and science applications to small, medium and heavy lift orbital vehicles. These new liquid fueled vehicles have LEO and GTO capabilities. Microcosm and the Scorpius Space Launch Company (SSLC) are well into the development of this all-new generation of expendable launch vehicles to support commercial and government missions. This paper presents the projected performance of the family of vehicles, status of the development program and projected launch service prices. The paper will discuss the new low cost ablative engines and low cost pressure-fed LOX/Jet-A propulsion systems. Schedules, payload volumes, dispensers, attach fittings, and planned dual manifest capabilities will be presented. The unique configuration of the wide base first stage allows fairings that may extend beyond the current 4-meters. The Scorpius family is designed to facilitate encapsulated payloads and launch-on-demand. The implications of these new operational procedures will be addressed, including the techniques that will be used to drive down the cost of access to space while improving reliability. The Scorpius family of low cost vehicles addresses the full range of payloads from 700 lbs. in the Sprite Mini-Lift to over 50,000 lbs. to LEO in the Heavy-Lift, and over 18,000 lbs. to GTO. Two sub-orbital vehicles have been developed and successfully launched, with the latest vehicle (SR-XM) launched in March of 2001 from White Sands Missile Range. Development of the family of vehicles commenced in 1993 under contracts with the Air Force Research Laboratory Space Vehicle Directorate after a number of years of independent studies and system engineering. The Sprite Mini-Lift Small Expendable Launch Vehicle (SELV) that utilizes the SR-XM technologies is planned for an initial launch in mid 2005 with larger, scaled-up vehicles to follow.

SPECS: Orbital debris removal

NASA Technical Reports Server (NTRS)

1991-01-01

The debris problem has reached a stage at which the risk to satellites and spacecraft has become substantial in low Earth orbit (LEO). This research discovered that small particles posed little threat to spacecraft because shielding can effectively prevent these particles from damaging the spacecraft. The research also showed that, even though collision with a large piece of debris could destroy the spacecraft, the large pieces of debris pose little danger because they can be tracked and the spacecraft can be maneuvered away from these pieces. Additionally, there are many current designs to capture and remove large debris particles from the space environment. From this analysis, it was decided to concentrate on the removal of medium-sized orbital debris, that is, those pieces ranging from 1 cm to 50 cm in size. The current design incorporates a transfer vehicle and a netting vehicle to capture the medium-sized debris. The system is based near an operational space station located at 28.5 deg inclination and 400 km altitude. The system uses ground-based tracking to determine the location of a satellite breakup or debris cloud. These data are uploaded to the transfer vehicle, which proceeds to rendezvous with the debris at a lower altitude parking orbit. Next, the netting vehicle is deployed, tracks the targeted debris, and captures it. After expending the available nets, the netting vehicle returns to the transfer vehicle for a new netting module and continues to capture more debris in the target area. Once all the netting modules are expended, the transfer vehicle returns to the space station's orbit where it is resupplied with new netting modules from a space shuttle load. The new modules are launched by the shuttle from the ground and the expended modules are taken back to Earth for removal of the captured debris, refueling, and repacking of the nets. Once the netting modules are refurbished, they are taken back into orbit for reuse. In a typical mission, the system has the ability to capture 50 pieces of orbital debris. One mission will take approximately six months and the system is designed to allow for a 30 deg inclination change on the outgoing and incoming trips of the transfer vehicle.

NASA study backs SSTO, urges shuttle phaseout

NASA Astrophysics Data System (ADS)

Asker, James R.

1994-03-01

A brief discusion of a Congressionally ordered NASA study on how to meet future US Government space launch needs is presented. Three options were examined: (1) improvement ofthe Space Shuttle; (2) development of expendable launch vehicles (ELVs); and (3) development of a single-stage-to-orbit (SSTO), manned vehicle that is reusable with advanced technology. After examining the three options, it was determined that the most economical approach to space access through the year 2030 would be to develop the SSTO vehicle and phase out Space Shuttle operations within 15 years and ELVs within 20 years. Other aspects of the study's findings are briefly covered.

KSC-02pd1577

NASA Image and Video Library

2002-10-18

KENNEDY SPACE CENTER, FLA. - A worker ties down the container with the TDRS-J spacecraft onto a transport vehicle. TDRS-J is the third in the current series of three Tracking and Data Relay Satellites designed to replenish the existing on-orbit fleet of six spacecraft, the first of which was launched in 1983. The Tracking and Data Relay Satellite System is the primary source of space-to-ground voice, data and telemetry for the Space Shuttle. It also provides communications with the International Space Station and scientific spacecraft in low-earth orbit such as the Hubble Space Telescope, and launch support for some expendable vehicles. This new advanced series of satellites will extend the availability of TDRS communications services until approximately 2017.

Space Shuttle capabilities, constraints, and cost

NASA Technical Reports Server (NTRS)

Lee, C. M.

1980-01-01

The capabilities, constraints, and costs of the Space Transportation System (STS), which combines reusable and expendable components, are reviewed, and an overview of the current planning activities for operating the STS in an efficient and cost-effective manner is presented. Traffic forecasts, performance constraints and enhancements, and potential new applications are discussed. Attention is given to operating costs, pricing policies, and the steps involved in 'getting on board', which includes all the interfaces between NASA and the users necessary to come to launch service agreements.

KSC-2012-1862

NASA Image and Video Library

2012-02-17

Satellites: The principal objectives of the Launch Services Program are to provide safe, reliable, cost-effective and on schedule launch services for NASA and NASA-sponsored payloads seeking launch on expendable vehicles. These payloads have a number of purposes. Scientific satellites obtain information about the space environment and transmit it to stations on Earth. Applications satellites designed to perform experiments that have everyday usefulness for people on Earth, such as weather forecasting and communications. Poster designed by Kennedy Space Center Graphics Department/Greg Lee. Credit: NASA

NASA Applications of Structural Health Monitoring Technology

NASA Technical Reports Server (NTRS)

Richards, W Lance; Madaras, Eric I.; Prosser, William H.; Studor, George

2013-01-01

This presentation provides examples of research and development that has recently or is currently being conducted at NASA, with a special emphasis on the application of structural health monitoring (SHM) of aerospace vehicles. SHM applications on several vehicle programs are highlighted, including Space Shuttle Orbiter, the International Space Station, Uninhabited Aerial Vehicles, and Expendable Launch Vehicles. Examples of current and previous work are presented in the following categories: acoustic emission impact detection, multi-parameter fiber optic strain-based sensing, wireless sensor system development, and distributed leak detection.

Space Launch System (SLS) Mission Planner's Guide

NASA Technical Reports Server (NTRS)

Smith, David Alan

2017-01-01

The purpose of this Space Launch System (SLS) Mission Planner's Guide (MPG) is to provide future payload developers/users with sufficient insight to support preliminary SLS mission planning. Consequently, this SLS MPG is not intended to be a payload requirements document; rather, it organizes and details SLS interfaces/accommodations in a manner similar to that of current Expendable Launch Vehicle (ELV) user guides to support early feasibility assessment. Like ELV Programs, once approved to fly on SLS, specific payload requirements will be defined in unique documentation.

KSC-02pd1947

NASA Image and Video Library

2002-12-17

KENNEDY SPACE CENTER, FLA. -- Attached underneath the Orbital Sciences L-1011 aircraft is the Pegasus XL Expendable Launch Vehicle, which will be transported to the Multi-Payload Processing Facility for testing and verification. The Pegasus will undergo three flight simulations prior to its scheduled launch in late January 2003. The Pegasus XL will carry NASA's Solar Radiation and Climate Experiment (SORCE) into orbit. Built by Orbital Sciences Space Systems Group, SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere. .

KSC-02pd1952

NASA Image and Video Library

2002-12-17

KENNEDY SPACE CENTER, FLA. -- Attached underneath the Orbital Sciences L-1011 aircraft is the Pegasus XL Expendable Launch Vehicle, which will be transported to the Multi-Payload Processing Facility for testing and verification. The Pegasus will undergo three flight simulations prior to its scheduled launch in late January 2003. The Pegasus XL will carry NASA's Solar Radiation and Climate Experiment (SORCE) into orbit. Built by Orbital Sciences Space Systems Group, SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere. .

Exobiology in Earth orbit: The results of science workshops held at NASA, Ames Research Center

NASA Technical Reports Server (NTRS)

Defrees, D. (Editor); Brownlee, D. (Editor); Tarter, J. (Editor); Usher, D. (Editor); Irvine, W. (Editor); Klein, H. (Editor)

1989-01-01

The Workshops on Exobiology in Earth Orbit were held to explore concepts for orbital experiments of exobiological interest and make recommendations on which classes of experiments should be carried out. Various observational and experimental opportunities in Earth orbit are described including those associated with the Space Shuttle laboratories, spacecraft deployed from the Space Shuttle and expendable launch vehicles, the Space Station, and lunar bases. Specific science issues and technology needs are summarized. Finally, a list of recommended experiments in the areas of observational exobiology, cosmic dust collection, and in situ experiments is presented.

Summary of the study of disposal of nuclear waste into space

NASA Technical Reports Server (NTRS)

Rom, F. E.

1973-01-01

The space shuttle together with expendable and nonexpendable orbital stages such as the space tug or Centaur can safely dispose of waste material by ejecting it from the solar system. The safety problems associated with all phases of launching and operation (normal, emergency, and accident) of such a system are being examined. It appears that solutions can be found that should make the risks acceptable when compared to the benefits to be obtained from the disposal of the nuclear waste. The techniques proposed to make such a system acceptable need to be carefully verified by further study and experiment.

Extended mission life support systems

NASA Technical Reports Server (NTRS)

Quattrone, P. D.

1985-01-01

Extended manned space missions which include interplanetary missions require regenerative life support systems. Manned mission life support considerations are placed in perspective and previous manned space life support system technology, activities and accomplishments in current supporting research and technology (SR&T) programs are reviewed. The life support subsystem/system technologies required for an enhanced duration orbiter (EDO) and a space operations center (SOC), regenerative life support functions and technology required for manned interplanetary flight vehicles, and future development requirements are outlined. The Space Shuttle Orbiters (space transportation system) is space cabin atmosphere is maintained at Earth ambient pressure of 14.7 psia (20% O2 and 80% N2). The early Shuttle flights will be seven-day flights, and the life support system flight hardware will still utilize expendables.

Air Force Reusable Booster System: A Quick-look, Design Focused Modeling and Cost Analysis Study

NASA Technical Reports Server (NTRS)

Zapata, Edgar

2011-01-01

This paper presents a method and an initial analysis of the costs of a reusable booster system (RBS) as envisioned by the US Department of Defense (DoD) and numerous initiatives that form the concept of Operationally Responsive Space (ORS). This paper leverages the knowledge gained from decades of experience with the semi-reusable NASA Space Shuttle to understand how the costs of a military next generation semi-reusable space transport might behave in the real world - and how it might be made as affordable as desired. The NASA Space Shuttle had a semi-expendable booster, that being the reusable Solid Rocket MotorslBoosters (SRMlSRB) and the expendable cryogenic External Tank (ET), with a reusable cargo and crew capable orbiter. This paper will explore DoD concepts that invert this architectural arrangement, using a reusable booster plane that flies back to base soon after launch, with the in-space elements of the launch system being the expendable portions. Cost estimating in the earliest stages of any potential, large scale program has limited usefulness. As a result, the emphasis here is on developing an approach, a structure, and the basic concepts that could continue to be matured as the program gains knowledge. Where cost estimates are provided, these results by necessity carry many caveats and assumptions, and this analysis becomes more about ways in which drivers of costs for diverse scenarios can be better understood. The paper is informed throughout with a design-for-cost philosophy whereby the design and technology features of the proposed RBS (who and what, the "architecture") are taken as linked at the hip to a desire to perform a certain mission (where and when), and together these inform the cost, responsiveness, performance and sustainability (how) of the system. Concepts for developing, acquiring, producing or operating the system will be shown for their inextricable relationship to the "architecture" of the system, and how these too relate to costs. Design and technology features bear special relevance to early program research and development directions. Given the uncertainties involved in both their actual performance promise and their relation to costs of operational systems, this later relationship is also given special attention.

Evolutionary space platform concept study. Volume 1: Executive summary

NASA Technical Reports Server (NTRS)

1982-01-01

The Evolutionary Space Platform Concept Study encompassed a 10 month effort to define, evaluate and compare approaches and concepts for evolving unmanned and manned capability platforms beyond the current Space Platform concepts to an evolutionary goal of establishing a permanent manned presence in space. Areas addressed included: special emphasis trade studies on the current unmanned concept, assessment of manned platform concepts, and utility analysis of a manned platform for defense related missions.

Assembly Platform For Use In Outer Space

NASA Technical Reports Server (NTRS)

Rao, Niranjan S.; Buddington, Patricia A.

1995-01-01

Report describes conceptual platform or framework for use in assembling other structures and spacecraft in outer space. Consists of three fixed structural beams comprising central beam and two cross beams. Robotic manipulators spaced apart on platform to provide telerobotic operation of platform by either space-station or ground crews. Platform and attached vehicles function synergistically to achieve maximum performance for intended purposes.

NASA Launch Services Program Overview

NASA Technical Reports Server (NTRS)

Higginbotham, Scott

2016-01-01

The National Aeronautics and Space Administration (NASA) has need to procure a variety of launch vehicles and services for its unmanned spacecraft. The Launch Services Program (LSP) provides the Agency with a single focus for the acquisition and management of Expendable Launch Vehicle (ELV) launch services. This presentation will provide an overview of the LSP and its organization, approach, and activities.

Delta Advanced Reusable Transport (DART): An alternative manned spacecraft

NASA Astrophysics Data System (ADS)

Lewerenz, T.; Kosha, M.; Magazu, H.

Although the current U.S. Space Transportation System (STS) has proven successful in many applications, the truth remains that the space shuttle is not as reliable or economical as was once hoped. In fact, the Augustine Commission on the future of the U.S. Space Program has recommended that the space shuttle only be used on missions directly requiring human capabilities on-orbit and that the shuttle program should eventually be phased out. This poses a great dilemma since the shuttle provides the only current or planned U.S. means for human access to space at the same time that NASA is building toward a permanent manned presence. As a possible solution to this dilemma, it is proposed that the U.S. begin development of an Alternative Manned Spacecraft (AMS). This spacecraft would not only provide follow-on capability for maintaining human space flight, but would also provide redundancy and enhanced capability in the near future. Design requirements for the AMS studied include: (1) capability of launching on one of the current or planned U.S. expendable launch vehicles (baseline McDonnell Douglas Delta II model 7920 expendable booster); (2) application to a wide variety of missions including autonomous operations, space station support, and access to orbits and inclinations beyond those of the space shuttle; (3) low enough costing to fly regularly in augmentation of space shuttle capabilities; (4) production surge capabilities to replace the shuttle if events require it; (5) intact abort capability in all flight regimes since the planned launch vehicles are not man-rated; (6) technology cut-off date of 1990; and (7) initial operational capability in 1995. In addition, the design of the AMS would take advantage of scientific advances made in the 20 years since the space shuttle was first conceived. These advances are in such technologies as composite materials, propulsion systems, avionics, and hypersonics.

Delta Advanced Reusable Transport (DART): An alternative manned spacecraft

NASA Technical Reports Server (NTRS)

Lewerenz, T.; Kosha, M.; Magazu, H.

1991-01-01

Although the current U.S. Space Transportation System (STS) has proven successful in many applications, the truth remains that the space shuttle is not as reliable or economical as was once hoped. In fact, the Augustine Commission on the future of the U.S. Space Program has recommended that the space shuttle only be used on missions directly requiring human capabilities on-orbit and that the shuttle program should eventually be phased out. This poses a great dilemma since the shuttle provides the only current or planned U.S. means for human access to space at the same time that NASA is building toward a permanent manned presence. As a possible solution to this dilemma, it is proposed that the U.S. begin development of an Alternative Manned Spacecraft (AMS). This spacecraft would not only provide follow-on capability for maintaining human space flight, but would also provide redundancy and enhanced capability in the near future. Design requirements for the AMS studied include: (1) capability of launching on one of the current or planned U.S. expendable launch vehicles (baseline McDonnell Douglas Delta II model 7920 expendable booster); (2) application to a wide variety of missions including autonomous operations, space station support, and access to orbits and inclinations beyond those of the space shuttle; (3) low enough costing to fly regularly in augmentation of space shuttle capabilities; (4) production surge capabilities to replace the shuttle if events require it; (5) intact abort capability in all flight regimes since the planned launch vehicles are not man-rated; (6) technology cut-off date of 1990; and (7) initial operational capability in 1995. In addition, the design of the AMS would take advantage of scientific advances made in the 20 years since the space shuttle was first conceived. These advances are in such technologies as composite materials, propulsion systems, avionics, and hypersonics.

UAH/NASA Workshop on Space Science Platform

NASA Technical Reports Server (NTRS)

Wu, S. T. (Editor); Morgan, S. (Editor)

1978-01-01

The scientific user requirements for a space science platform were defined. The potential user benefits, technological implications and cost of space platforms were examined. Cost effectiveness of the platforms' capabilities were also examined.

14 CFR 420.19 - Launch site location review-general.

Code of Federal Regulations, 2010 CFR

2010-01-01

... site, at least one type of expendable or reusable launch vehicle can be flown from the launch point... × 10−6). (2) Types of launch vehicles include orbital expendable launch vehicles, guided sub-orbital expendable launch vehicles, unguided sub-orbital expendable launch vehicles, and reusable launch vehicles...

24 CFR 84.35 - Supplies and other expendable property.

Code of Federal Regulations, 2010 CFR

2010-04-01

... 24 Housing and Urban Development 1 2010-04-01 2010-04-01 false Supplies and other expendable... Standards § 84.35 Supplies and other expendable property. (a) Title to supplies and other expendable property shall vest in the recipient upon acquisition. If there is a residual inventory of unused supplies...

Evolutionary space platform concept study. Volume 2, part B: Manned space platform concepts

NASA Technical Reports Server (NTRS)

1982-01-01

Logical, cost-effective steps in the evolution of manned space platforms are investigated and assessed. Tasks included the analysis of requirements for a manned space platform, identifying alternative concepts, performing system analysis and definition of the concepts, comparing the concepts and performing programmatic analysis for a reference concept.

Summary of the study of disposal of nuclear waste into space

NASA Technical Reports Server (NTRS)

Rom, F. E.

1973-01-01

NASA, at the request of the AEC, is conducting a preliminary study to determine the feasibility of disposing of nuclear waste material into space. The study has indicated that the Space Shuttle together with expendable and nonexpendable orbital stages such as the Space Tug or Centaur can safety dispose of waste material by ejecting it from the solar system. The safety problems associated with all phases of launching and operation (normal, emergency and accident) of such a system are being examined. From the preliminary study it appears that solutions can be found that should make the risks acceptable when compared to the benefits to be obtained from the disposal of the nuclear waste.

Artist's Concept of X-37 Re-entry

NASA Technical Reports Server (NTRS)

1999-01-01

Pictured is an artist's concept of the experimental X-37 Reusable Launch Vehicle re-entering Earth`s atmosphere. NASA and the Boeing Company entered a cooperative agreement to develop and fly a new experimental space plane called the X-37 that would be ferried into orbit to test new technologies. The reusable space plane incorporated technologies aimed at significantly cutting the cost of space flight. The X-37 would be carried into orbit by the Space Shuttle or be launched by an expendable rocket. After the X-37 was deployed, it would remain in orbit up to 21 days, performing a variety of experiments before re-entering the Earth's atmosphere and landing. The X-37 program was discontinued in 2003.

Advanced Concept

NASA Image and Video Library

1999-08-13

Pictured is an artist's concept of the experimental X-37 Reusable Launch Vehicle re-entering Earth‘s atmosphere. NASA and the Boeing Company entered a cooperative agreement to develop and fly a new experimental space plane called the X-37 that would be ferried into orbit to test new technologies. The reusable space plane incorporated technologies aimed at significantly cutting the cost of space flight. The X-37 would be carried into orbit by the Space Shuttle or be launched by an expendable rocket. After the X-37 was deployed, it would remain in orbit up to 21 days, performing a variety of experiments before re-entering the Earth's atmosphere and landing. The X-37 program was discontinued in 2003.

Aeronautics and Space Report of the President

NASA Technical Reports Server (NTRS)

1990-01-01

Nineteen eighty-eight marked the United States' return to space flight with two successful space shuttle launches in September and December, as well as six successful expendable rocket launches. Meanwhile, many other less spectacular but important contributions were made in aeronautics and space by the 14 participating government organizations. Each organization's aeronautics and/or space activities for the year are presented. The organizations involved include: (1) NASA; (2) Department of Defense; (3) Department of Commerce; (4) Department of Energy; (5) Department of the Interior; (6) Department of Agriculture; (7) Federal Communications Commission; (8) Department of Transportation; (9) Environmental Protection Agency; (10) National Science Foundation; (11) Smithsonian Institution; (12) Department of State; (13) Arms Control and Disarmament Agency; and (14) United States Information Agency.

Making Data Work Harder: OCLC Shows How Data Mined from Systems like WorldCat Can Add Value for Librarians and Users

ERIC Educational Resources Information Center

Lavoie, Brian; Dempsey, Lorcan; Connaway, Lynn Silipigni

2006-01-01

If librarians want to improve their visibility and value in the increasingly crowded digital information spaces, where users expect good results without expending much time or effort, they must learn to repurpose data to create added value. Since librarians already possess valuable data sources, like circulation statistics, reference transactions,…

Apollo 7/S-IVB Rendezvous in space

NASA Technical Reports Server (NTRS)

1968-01-01

The expended Saturn IVB stage as photographed from the Apollo 7 spacecraft during transposition and docking maneuvers. This photograph was taken over Sonora, Mexico, during Apollo 7's second revolution of the Earth. The round, white disc inside the open panels of the Saturn IVB is a simulated docking target similar to that used on the lunar module for docking during lunar missions.

KSC-03pd0024

NASA Image and Video Library

2003-01-05

KENNEDY SPACE CENTER, FLA. - Technicians in the Multi-Purpose Processing Facility move NASA's Solar Radiation and Climate Experiment (SORCE) toward the Pegasus XL Expendable Launch Vehicle for mating. SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere. The launch of SORCE is scheduled for Jan. 25 at 3:14 p.m. from Cape Canaveral Air Force Station, Fla.

KSC-03pd0025

NASA Image and Video Library

2003-01-05

KENNEDY SPACE CENTER, FLA. -- In the Multi-Purpose Processing Facility, NASA's Solar Radiation and Climate Experiment (SORCE) closes in on the Pegasus XL Expendable Launch Vehicle for mating. SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere. The launch of SORCE is scheduled for Jan. 25 at 3:14 p.m. from Cape Canaveral Air Force Station, Fla.

KSC-03pd0026

NASA Image and Video Library

2003-01-05

KENNEDY SPACE CENTER, FLA. -- In the Multi-Purpose Processing Facility, NASA's Solar Radiation and Climate Experiment (SORCE) closes in on the Pegasus XL Expendable Launch Vehicle for mating. SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere. The launch of SORCE is scheduled for Jan. 25 at 3:14 p.m. from Cape Canaveral Air Force Station, Fla.

Space Suit Radiator Performance in Lunar and Mars Environments

NASA Technical Reports Server (NTRS)

Nabity, James; Mason, Georgia; Copeland, Robert; Libberton, Kerry; Stephan, Ryan; Trevino, Luis; Paul, Heather

2005-01-01

During an ExtraVehicular Activity (EVA), both the heat generated by the astronaut's metabolism and that produced by the Portable Life Support System (PLSS) must be rejected to space. The heat sources include the heat of adsorption of metabolic CO2, the heat of condensation of water, the heat removed from the body by the liquid cooling garment and the load from the electrical components. Although the sublimator hardware to reject this load weighs only 1.58 kg (3.48 lbm), an additional 3.6 kg (8 lbm) of water are loaded into the unit, most of which is sublimated and lost to thus become the single largest expendable during an eight hour EVA. We can significantly reduce the amount of expendable water consumed in the sublimator by using a radiator to reject heat from the Astronaut during an EVA. Last year we reported on the design and initial operational assessment tests of our novel radiator designated the Radiator And Freeze Tolerant heat eXchanger (RAFT-X). Herein, we report on tests conducted in the NASA Johnson Space Center Chamber E Thermal Vacuum Test Facility. Up to 260 W (900 Btu/h) of heat were rejected in Lunar and Mars environments with temperatures as cold as -170 C (- 275 F). Further, the RAFT-X endured several freeze / thaw cycles and in fact, the heat exchanger was completely frozen three times without any apparent damage to the unit.

KSC-05PD-0502B

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. At Astrotech in Titusville, Fla., Boeing technicians hold guide wires attached to the crane lifting the GOES-N satellite. Since its arrival on March 11, the satellite has been undergoing final testing by Boeing Satellite Systems of the imaging system, instrumentation, communications and power systems. Geostationary Operational Environmental Satellites (GOES) are sponsored by NASAs Goddard Space Flight Center and the National Oceanic and Atmospheric Administration. GOES-N is targeted to launch May 4 onboard a Boeing expendable launch vehicle Delta IV (4,2) with a 3-burn second stage operation.

Russian Soyuz in Launch Position

NASA Technical Reports Server (NTRS)

2000-01-01

The Soyuz TM-31 launch vehicle is shown in the vertical position for its launch from Baikonur, carrying the first resident crew to the International Space Station. The Russian Soyuz launch vehicle is an expendable spacecraft that evolved out of the original Class A (Sputnik). From the early 1960s until today, the Soyuz launch vehicle has been the backbone of Russia's marned and unmanned space launch fleet. Today, the Soyuz launch vehicle is marketed internationally by a joint Russian/French consortium called STARSEM. As of August 2001, there have been ten Soyuz missions under the STARSEM banner.

KSC-02pd1946

NASA Image and Video Library

2002-12-17

KENNEDY SPACE CENTER, FLA. - An Orbital Sciences L-1011 aircraft arrives at the Cape Canaveral Air Force Station Skid Strip. Attached underneath the aircraft is the Pegasus XL Expendable Launch Vehicle, which will be transported to the Multi-Payload Processing Facility for testing and verification. The Pegasus will undergo three flight simulations prior to its scheduled launch in late January 2003. The Pegasus XL will carry NASA's Solar Radiation and Climate Experiment (SORCE) into orbit. Built by Orbital Sciences Space Systems Group, SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere. .

KSC-02pd1951

NASA Image and Video Library

2002-12-17

KENNEDY SPACE CENTER, FLA. -- Workers at the Cape Canaveral Air Force Station Skid Strip stand next to the Pegasus XL Expendable Launch Vehicle underneath the Orbital Sciences L-1011 aircraft. The Pegasus will be transported to the Multi-Payload Processing Facility for testing and verification. The Pegasus will undergo three flight simulations prior to its scheduled launch in late January 2003. The Pegasus XL will carry NASA's Solar Radiation and Climate Experiment (SORCE) into orbit. Built by Orbital Sciences Space Systems Group, SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere. .

Chronology of KSC and KSC related events for 1984

NASA Technical Reports Server (NTRS)

Nail, K., Jr.

1985-01-01

In his third State of the Union address, President Reagan told NASA to develop a permanent manned space station in 10 years. The President also ordered the Department of Transportation to help private firms launch rockets, thus introducing the commercialization of space. There were five space shuttle and six expendable vehicle launches in 1984. Materials were selected from a number of published sources. The document records KSC events of interest to historians and other researchers. Arrangement is by month; items are by date of the published sources. Actual date of the event may be indicated in parenthesis, when the article itself does not make that information explicit.

KSC-02pd2005

NASA Image and Video Library

2002-12-18

KENNEDY SPACE CENTER, FLA. -- Workers prepare a Pegasus XL Expendable Launch Vehicle for detachment from the underside of an Orbital Sciences L-1011 aircraft. The aircraft, with the launch vehicle nestled beneath, arrived at the Cape Canaveral Air Force Station Skid Strip on Dec. 17. The Pegasus XL will undergo three flight simulations prior to its scheduled launch in late January 2003. It will carry NASA's Solar Radiation and Climate Experiment (SORCE) spacecraft into orbit. Built by Orbital Sciences Space Systems Group, SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere with instruments built by the University of Colorado's Laboratory for Atmospheric and Space Physics (LASP).

KSC-02pd2001

NASA Image and Video Library

2002-12-18

KENNEDY SPACE CENTER, FLA. -- Workers prepare to remove a Pegasus XL Expendable Launch Vehicle from the underside of an Orbital Sciences L-1011 aircraft. The aircraft, with the launch vehicle attached, arrived at the Cape Canaveral Air Force Station Skid Strip on Dec. 17. The Pegasus XL will undergo three flight simulations prior to its scheduled launch in late January 2003. It will carry NASA's Solar Radiation and Climate Experiment (SORCE) spacecraft into orbit. Built by Orbital Sciences Space Systems Group, SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere with instruments built by the University of Colorado's Laboratory for Atmospheric and Space Physics (LASP).

Organizing for low cost space transportation

NASA Technical Reports Server (NTRS)

Lee, C. M.

1977-01-01

The paper describes the management concepts and organizational structure NASA is establishing to operate the Space Transportation System. Policies which would encourage public and commercial organizations and private individuals to use the new STS are discussed, and design criteria for experiments, spacecraft, and other systems elements are considered. The design criteria are intented to facilitate cost reductions for space operations. NASA plans for the transition from currently used expendable launch vehicles to Shuttle use and Shuttle pricing policies are explained in detail. Hardware development is basically complete, management functions have been defined, pricing policies have been published, and procedures for user contact and services have been places into operation.

Advanced regenerative environmental control and life support systems - Air and water regeneration

NASA Technical Reports Server (NTRS)

Schubert, F. H.; Wynveen, R. A.; Quattrone, P. D.

1984-01-01

Extended manned space missions will require regenerative life support techniques. Past U.S. manned missions used nonregenerative expendables, except for a molecular sieve-based carbon dioxide removal system aboard Skylab. The resupply penalties associated with expandables becomes prohibitive as crew size and mission duration increase. The U.S. Space Station, scheduled to be operational in the 1990's, is based on a crew of four to sixteen and a resupply period of 90 days or greater. It will be the first major spacecraft to employ regenerable techniques for life support. The paper uses the requirements for the Space Station to address these techniques.

KSC-02pd2002

NASA Image and Video Library

2002-12-18

KENNEDY SPACE CENTER, FLA. -- A Pegasus XL Expendable Launch Vehicle is moments away from being removed from the underside of an Orbital Sciences L-1011 aircraft. The aircraft, with the launch vehicle attached, arrived at the Cape Canaveral Air Force Station Skid Strip on Dec. 17. The Pegasus XL will undergo three flight simulations prior to its scheduled launch in late January 2003. It will carry NASA's Solar Radiation and Climate Experiment (SORCE) spacecraft into orbit. Built by Orbital Sciences Space Systems Group, SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere with instruments built by the University of Colorado's Laboratory for Atmospheric and Space Physics (LASP).

KSC-02pd2003

NASA Image and Video Library

2002-12-18

KENNEDY SPACE CENTER, FLA. -- Workers begin the process to remove a Pegasus XL Expendable Launch Vehicle from the underside of an Orbital Sciences L-1011 aircraft. The aircraft, with the launch vehicle attached, arrived at the Cape Canaveral Air Force Station Skid Strip on Dec. 17. The Pegasus XL will undergo three flight simulations prior to its scheduled launch in late January 2003. It will carry NASA's Solar Radiation and Climate Experiment (SORCE) spacecraft into orbit. Built by Orbital Sciences Space Systems Group, SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere with instruments built by the University of Colorado's Laboratory for Atmospheric and Space Physics (LASP).

Orbiter processing facility: Access platforms Kennedy Space Center, Florida, from challenge to achievement

NASA Technical Reports Server (NTRS)

Haratunian, M.

1985-01-01

A system of access platforms and equipment within the space shuttle orbiter processing facility at Kennedy Space Center is described. The design challenges of the platforms, including clearance envelopes, load criteria, and movement, are discussed. Various applications of moveable platforms are considered.

Hyperspectral range imaging for transportation systems evaluation

NASA Astrophysics Data System (ADS)

Bridgelall, Raj; Rafert, J. B.; Atwood, Don; Tolliver, Denver D.

2016-04-01

Transportation agencies expend significant resources to inspect critical infrastructure such as roadways, railways, and pipelines. Regular inspections identify important defects and generate data to forecast maintenance needs. However, cost and practical limitations prevent the scaling of current inspection methods beyond relatively small portions of the network. Consequently, existing approaches fail to discover many high-risk defect formations. Remote sensing techniques offer the potential for more rapid and extensive non-destructive evaluations of the multimodal transportation infrastructure. However, optical occlusions and limitations in the spatial resolution of typical airborne and space-borne platforms limit their applicability. This research proposes hyperspectral image classification to isolate transportation infrastructure targets for high-resolution photogrammetric analysis. A plenoptic swarm of unmanned aircraft systems will capture images with centimeter-scale spatial resolution, large swaths, and polarization diversity. The light field solution will incorporate structure-from-motion techniques to reconstruct three-dimensional details of the isolated targets from sequences of two-dimensional images. A comparative analysis of existing low-power wireless communications standards suggests an application dependent tradeoff in selecting the best-suited link to coordinate swarming operations. This study further produced a taxonomy of specific roadway and railway defects, distress symptoms, and other anomalies that the proposed plenoptic swarm sensing system would identify and characterize to estimate risk levels.

Space Station

NASA Image and Video Library

1981-12-01

During 1980 and the first half of 1981, the Marshall Space Flight Center conducted studies concerned with a relatively low-cost, near-term, manned space platform to satisfy current user needs, yet capable of evolutionary growth to meet future needs. The Science and Application Manned Space Platform (SAMSP) studies were to serve as a test bed for developing scientific and operational capabilities required by later, more advanced manned platforms while accomplishing early science and operations. This concept illustrates a manned space platform.

Large Space Systems Technology, 1979. [antenna and space platform systems conference

NASA Technical Reports Server (NTRS)

Ward, J. C., Jr. (Compiler)

1980-01-01

Items of technology and developmental efforts in support of the large space systems technology programs are described. The major areas of interest are large antennas systems, large space platform systems, and activities that support both antennas and platform systems.

Space Station

NASA Image and Video Library

1982-01-01

McDornel Douglas performed an Evolutionary Space Platform Concept Study for the Marshall Space Flight Center in the early 1980's. The 10-month study was designed to define, evaluate, and compare approaches and concepts for evolving unmanned and manned capability platforms beyond the then current space platform concepts to an evolutionary goal of establishing a permanent-manned presence in space.

A Freezable Heat Exchanger for Space Suit Radiator Systems

NASA Technical Reports Server (NTRS)

Nabity, James A.; Mason, Georgia R.; Copeland, Robert J.; Trevino, Luis a.

2008-01-01

During an ExtraVehicular Activity (EVA), both the heat generated by the astronaut s metabolism and that produced by the Portable Life Support System (PLSS) must be rejected to space. The heat sources include the heat of adsorption of metabolic CO2, the heat of condensation of water, the heat removed from the body by the liquid cooling garment and the load from the electrical components. Although the sublimator hardware to reject this load weighs only 1.58 kg (3.48 lbm), an additional 3.6 kg (8 lbm) of water are loaded into the unit, most of which is sublimated and lost to space, thus becoming the single largest expendable during an eight-hour EVA. Using a radiator to reject heat from the astronaut during an EVA can reduce the amount of expendable water consumed in the sublimator. Radiators have no moving parts and are thus highly reliable. Past freezable radiators have been too heavy, but the weight can be greatly reduced by placing a small and freeze tolerant heat exchanger between the astronaut and radiator, instead of making the very large radiator freeze tolerant. Therefore, the key technological innovation to improve space suit radiator performance was the development of a lightweight and freezable heat exchanger that accommodates the variable heat load generated by the astronaut. Herein, we present the heat transfer performance of a newly designed heat exchanger that endured several freeze / thaw cycles without any apparent damage. The heat exchanger was also able to continuously turn down or turn up the heat rejection to follow the variable load.

KSC-03pd0027

NASA Image and Video Library

2003-01-05

KENNEDY SPACE CENTER, FLA. - Workers in the Multi-Purpose Processing Facility move the rotating work stand away from NASA's Solar Radiation and Climate Experiment (SORCE) after mating with the Pegasus XL Expendable Launch Vehicle. SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere. The launch of SORCE is scheduled for Jan. 25 at 3:14 p.m. from Cape Canaveral Air Force Station, Fla.

KSC-03pd0028

NASA Image and Video Library

2003-01-05

KENNEDY SPACE CENTER, FLA. - A worker in the Multi-Purpose Processing Facility checks out the mating of NASA's Solar Radiation and Climate Experiment (SORCE) with the Pegasus XL Expendable Launch Vehicle. SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere. The launch of SORCE is scheduled for Jan. 25 at 3:14 p.m. from Cape Canaveral Air Force Station, Fla.

Space transportation, satellite services, and space platforms

NASA Technical Reports Server (NTRS)

Disher, J. H.

1979-01-01

The paper takes a preview of the progressive development of vehicles for space transportation, satellite services, and orbital platforms. A low-thrust upper stage of either the ion engine or chemical type will be developed to transport large spacecraft and space platforms to and from GEO. The multimission spacecraft, space telescope, and other scientific platforms will require orbital serves going beyond that provided by the Shuttle's remote manipulator system, and plans call for extravehicular activity tools, improved remote manipulators, and a remote manned work station (the cherry picker).

Application of Probabilistic Risk Assessment (PRA) During Conceptual Design for the NASA Orbital Space Plane (OSP)

NASA Technical Reports Server (NTRS)

Rogers, James H.; Safie, Fayssal M.; Stott, James E.; Lo, Yunnhon

2004-01-01

In order to meet the space transportation needs for a new century, America's National Aeronautics and Space Administration (NASA) has implemented an Integrated Space Transportation Plan to produce safe, economical, and reliable access to space. One near term objective of this initiative is the design and development of a next-generation vehicle and launch system that will transport crew and cargo to and from the International Space Station (ISS), the Orbital Space Plane (OSP). The OSP system is composed of a manned launch vehicle by an existing Evolved Expendable Launch Vehicle (EELV). The OSP will provide emergency crew rescue from the ISS by 2008, and provide crew and limited cargo transfer to and from the ISS by 2012. A key requirement is for the OSP to be safer and more reliable than the Soyuz and Space Shuttle, which currently provide these capabilities.

Office of Commercial Programs' research activities for Space Station Freedom utilization

NASA Technical Reports Server (NTRS)

Fountain, James A.

1992-01-01

One of the objectives of the Office of Commercial Programs (OCP) is to encourage, enable, and help implement space research which meets the needs of the U.S. industrial sector. This is done mainly through seventeen Centers for the Commercial Development of Space (CCDS's) which are located throughout the United States. The CCDS's are composed of members from U.S. companies, universities, and other government agencies. These Centers are presently engaged in industrial research in space using a variety of carriers to reach low Earth orbit. One of the goals is to produce a body of experience and knowledge that will allow U.S. industrial entities to make informed decisions regarding their participation in commercial space endeavors. A total of 32 items of payload hardware were built to date. These payloads have flown in space a total of 73 times. The carriers range from the KC-135 parabolic aircraft and expendable launch vehicles to the Space Shuttle. This range of carriers allows the experimenter to evolve payloads in complexity and cost by progressively extending the time in microgravity. They can start with a few seconds in the parabolic aircraft and go to several minutes on the rocket flights, before they progress to the complexities of manned flight on the Shuttle. Next year, two new capabilities will become available: COMET, an expendable-vehicle-launched experiment capsule that can carry experiments aloft for thirty days; and SPACEHAB, a new Shuttle borne module which will greatly add to the capability to accommodate small payloads. All of these commercial research activities and carrier capabilities are preparing the OCP to evolve those experiments that prove successful to Space Station Freedom. OCP and the CCDS's are actively involved in Space Station design and utilization planning and have proposed a set of experiments to be launched in 1996 and 1997. These experiments are to be conducted both internal and external to Space Station Freedom and will investigate industrial research topics which range from biotechnology to electronic materials to metallurgy. Some will be designed to make maximum use of the quiescent microgravity conditions in the 'ground-tended' phases during the early years of Space Station Freedom operations.

A multiple pointing-mount control strategy for space platforms

NASA Technical Reports Server (NTRS)

Johnson, C. D.

1992-01-01

A new disturbance-adaptive control strategy for multiple pointing-mount space platforms is proposed and illustrated by consideration of a simplified 3-link dynamic model of a multiple pointing-mount space platform. Simulation results demonstrate the effectiveness of the new platform control strategy. The simulation results also reveal a system 'destabilization phenomena' that can occur if the set of individual platform-mounted experiment controllers are 'too responsive.'

Future Concepts for Integrating the Space Launch System and the Multi-Purpose Crew Vehicle into a Reusable Space Transportation Infrastructure

NASA Technical Reports Server (NTRS)

Smitherman, David; Woodcock, Gordon

2012-01-01

A space transportation infrastructure is described that utilizes the Space Launch System (SLS), the Mulit-Purpose Crew Vehicle (MPCV), the International Space Station (ISS), and propellant depot servicing platforms to support all foreseeable missions in the Earth-Moon vicinity and deep space out to Mars. The infrastructure utilizes current expendable launch vehicle (ELV) systems such as the Delta IV Heavy, Atlas V, and Falcon 9, for commercial crew, cargo, and propellant launches to a Low-Earth-Orbit (LEO) Depot and/or the ISS. The SLS provides all payload and propellant launches to the Earth-Moon Langrange Point 1 (EML1) Depot to support new reusable in-space transportation vehicles. The ISS or follow-on LEO Depot supports missions to Geosynchronous Earth Orbit (GEO) for satellite servicing and to Earth-Moon L1 for EML1 Depot missions. The EML1 Depot supports Lunar, Earth-Sun L2 (ESL2), Asteroid, and Mars missions. New vehicle design concepts are presented that can be launched utilizing the SLS and current ELV systems. These new reusable vehicle concepts include a Crew Transfer Vehicle (CTV) derived from the MPCV and a reusable Cryogenic Propulsion Stage (CPS) for crew transportation between the LEO Depot, EML1 Depot and missions beyond the Earth-Moon vicinity; a new reusable Lunar Lander for crew transportation between the EML1 Depot and the lunar surface; and a new reusable Deep Space Habitat (DSH) with a CTV to support crew missions from the EML1 Depot to ESL2, Asteroids, and a Mars Orbital Depot. The LEO Depot, EML1 Depot, and Mars Orbital Depot are based on International Space Station (ISS) heritage hardware. Data provided includes the number of launches required for each mission utilizing SLS and current ELV systems (Delta IV Heavy or equivalent) and the approximate vehicle masses and propellant requirements. Also included is a discussion on affordability with ideas on technologies that could reduce the number of launches required and thoughts on how this infrastructure might be implemented incrementally over the next few decades. The potential benefits of this infrastructure include competitive bidding for ELV flights and propellant services, development of new reusable in-space vehicles, and development of a robust multiuse infrastructure that can support many government and commercial missions simultaneously.

KSC-02pd2016

NASA Image and Video Library

2002-12-18

KENNEDY SPACE CENTER, FLA. -- A Pegasus XL Expendable Launch Vehicle is prepared for towing to the Multi-Purpose Payload Facility (MPPF) where it will undergo testing, verification, and three flight simulations prior to its scheduled launch. The vehicle, nestled beneath an Orbital Sciences L-1011 aircraft, arrived at the Cape Canaveral Air Force Station Skid Strip on Dec. 17. It is commissioned to carry NASA's Solar Radiation and Climate Experiment (SORCE) spacecraft into orbit in late January 2003. Built by Orbital Sciences Space Systems Group, SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere with instruments built by the University of Colorado's Laboratory for Atmospheric and Space Physics (LASP).

KSC-02pd2007

NASA Image and Video Library

2002-12-18

KENNEDY SPACE CENTER, FLA. -- Workers supervise the placement of a transporter below a Pegasus XL Expendable Launch Vehicle before its detachment from the underside of an Orbital Sciences L-1011 aircraft. The aircraft, with the launch vehicle nestled beneath, arrived at the Cape Canaveral Air Force Station Skid Strip on Dec. 17. The Pegasus XL will undergo three flight simulations prior to its scheduled launch in late January 2003. It will carry NASA's Solar Radiation and Climate Experiment (SORCE) spacecraft into orbit. Built by Orbital Sciences Space Systems Group, SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere with instruments built by the University of Colorado's Laboratory for Atmospheric and Space Physics (LASP).

KSC-02pd2018

NASA Image and Video Library

2002-12-18

KENNEDY SPACE CENTER, FLA. -- A Pegasus XL Expendable Launch Vehicle sits atop a transporter following its arrival in the Multi-Purpose Payload Facility (MPPF) where it will undergo testing, verification, and three flight simulations prior to its scheduled launch. The vehicle, nestled beneath an Orbital Sciences L-1011 aircraft, arrived at the Cape Canaveral Air Force Station Skid Strip on Dec. 17. It is commissioned to carry NASA's Solar Radiation and Climate Experiment (SORCE) spacecraft into orbit in late January 2003. Built by Orbital Sciences Space Systems Group, SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere with instruments built by the University of Colorado's Laboratory for Atmospheric and Space Physics (LASP).

KSC-02pd2012

NASA Image and Video Library

2002-12-18

KENNEDY SPACE CENTER, FLA. -- Workers complete the final steps to detach a Pegasus XL Expendable Launch Vehicle from the underside of an Orbital Sciences L-1011 aircraft. The aircraft, with the launch vehicle nestled beneath, arrived at the Cape Canaveral Air Force Station Skid Strip on Dec. 17. The Pegasus XL will undergo three flight simulations prior to its scheduled launch in late January 2003. It will carry NASA's Solar Radiation and Climate Experiment (SORCE) spacecraft into orbit. Built by Orbital Sciences Space Systems Group, SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere with instruments built by the University of Colorado's Laboratory for Atmospheric and Space Physics (LASP).

KSC-02pd2010

NASA Image and Video Library

2002-12-18

KENNEDY SPACE CENTER, FLA. -- A transporter is repositioned below a Pegasus XL Expendable Launch Vehicle before it is detached from the underside of an Orbital Sciences L-1011 aircraft. The aircraft, with the launch vehicle nestled beneath, arrived at the Cape Canaveral Air Force Station Skid Strip on Dec. 17. The Pegasus XL will undergo three flight simulations prior to its scheduled launch in late January 2003. It will carry NASA's Solar Radiation and Climate Experiment (SORCE) spacecraft into orbit. Built by Orbital Sciences Space Systems Group, SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere with instruments built by the University of Colorado's Laboratory for Atmospheric and Space Physics (LASP).

KSC-02pd2015

NASA Image and Video Library

2002-12-18

KENNEDY SPACE CENTER, FLA. -- A Pegasus XL Expendable Launch Vehicle is prepared for towing to the Multi-Purpose Payload Facility (MPPF) where it will undergo testing, verification, and three flight simulations prior to its scheduled launch. The vehicle, nestled beneath an Orbital Sciences L-1011 aircraft, arrived at the Cape Canaveral Air Force Station Skid Strip on Dec. 17. It is commissioned to carry NASA's Solar Radiation and Climate Experiment (SORCE) spacecraft into orbit in late January 2003. Built by Orbital Sciences Space Systems Group, SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere with instruments built by the University of Colorado's Laboratory for Atmospheric and Space Physics (LASP).

KSC-02pd2006

NASA Image and Video Library

2002-12-18

KENNEDY SPACE CENTER, FLA. -- A transporter is positioned below a Pegasus XL Expendable Launch Vehicle before its detachment from the underside of an Orbital Sciences L-1011 aircraft. The aircraft, with the launch vehicle nestled beneath, arrived at the Cape Canaveral Air Force Station Skid Strip on Dec. 17. The Pegasus XL will undergo three flight simulations prior to its scheduled launch in late January 2003. It will carry NASA's Solar Radiation and Climate Experiment (SORCE) spacecraft into orbit. Built by Orbital Sciences Space Systems Group, SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere with instruments built by the University of Colorado's Laboratory for Atmospheric and Space Physics (LASP).

Space Shuttle utilization characteristics with special emphasis on payload design, economy of operation and effective space exploitation

NASA Technical Reports Server (NTRS)

Turner, D. N.

1981-01-01

The reusable manned Space Shuttle has made new and innovative payload planning a reality and opened the door to a variety of payload concepts formerly unavailable in routine space operations. In order to define the payload characteristics and program strategies, current Shuttle-oriented programs are presented: NASA's Space Telescope, the Long Duration Exposure Facility, the West German Shuttle Pallet Satellite, and the Goddard Space Flight Center's Multimission Modular Spacecraft. Commonality of spacecraft design and adaptation for specific mission roles minimizes payload program development and STS integration costs. Commonality of airborne support equipment assures the possibility of multiple program space operations with the Shuttle. On-orbit maintenance and repair was suggested for the module and system levels. Program savings from 13 to over 50% were found obtainable by the Shuttle over expendable launch systems, and savings from 17 to 45% were achievable by introducing reuse into the Shuttle-oriented programs.

Turnaround operations analysis for OTV. Volume 1: Executive summary

NASA Technical Reports Server (NTRS)

1988-01-01

Anaylses performed for ground processing, both expendable and reusable ground-based Orbital Transfer Vehicles (OTVs) launched on the Space Transportation System (STS), a reusable space-based OTV (SBOTV) launched on the STS, and a reusable ground-based OTV (GBOTV) launched on an unmanned cargo vehicle and recovered by the Orbiter are summarized. Also summarized are the analyses performed for space processing the reusable SBOTV at the Space Station in low Earth orbit (LEO) as well as the maintenance and servicing of the SBOTV accommodations at the Space Station. In addition, the candidate OTV concepts, design and interface requirements, and the Space Station design, support, and interface requirements are summarized. A development schedule and associated costs for the required SBOTV accommodations at the Space Station are presented. Finallly, the technology development plan to develop the capability to process both GBOTVs and SBOTVs are summarized.

Space transportation systems within ESA programmes: Current status and perspectives

NASA Astrophysics Data System (ADS)

Delahais, Maurice

1993-03-01

An overview of the space transportation aspects of the ESA (European Space Agency) programs as they result from history, present status, and decisions taken at the ministerial level conference in Granada, Spain is presented. The new factors taken into consideration for the long term plan proposed in Munich, Germany, the three strategic options for the reorientation of the ESA long term plan, and the essential elements of space transportation in the Granada long term plan in three areas of space activities, scientific, and commercial launches with expendable launch vehicles, manned flight and in-orbit infrastructure, and future transportation systems are outlined. The new ESA long term plan, in the field of space transportation systems, constitutes a reorientation of the initial program contemplated in previous councils at ministerial level. It aims at balancing the new economic situation with the new avenues of cooperation, and the outcome will be a new implementation of the space transportation systems policy.

Organizing for low cost space operations - Status and plans

NASA Technical Reports Server (NTRS)

Lee, C.

1976-01-01

Design features of the Space Transportation System (vehicle reuse, low cost expendable components, simple payload interfaces, standard support systems) must be matched by economical operational methods to achieve low operating and payload costs. Users will be responsible for their own payloads and will be charged according to the services they require. Efficient use of manpower, simple documentation, simplified test, checkout, and flight planning are firm goals, together with flexibility for quick response to varying user needs. Status of the Shuttle hardware, plans for establishing low cost procedures, and the policy for user charges are discussed.

Study of alternate space shuttle concepts

NASA Technical Reports Server (NTRS)

1971-01-01

A study of alternate space shuttle concepts was conducted to examine the stage-and-one-half concept and its potential for later conversion and use in the two stage reusable shuttle system. A study of external hydrogen tank concepts was conducted to determine the issues involved in the design and production of a low-cost expendable tank system. The major objectives of the study were to determine: (1) realistic drop tank program cost estimates, (2) estimated drop tank program cost for selected specific designs, and (3) change in program cost due to variations in design and manufacturing concepts and changes in program assumptions.

The StarBooster System: A Cargo Aircraft for Space

NASA Technical Reports Server (NTRS)

Davis, Hubert P.; Dula, Arthur M.; McLaughlin, Don; Frassanito, John; Andrews, Jason (Editor)

1999-01-01

Starcraft Boosters has developed a different approach for lowering the cost of access to space. We propose developing a new aircraft that will house an existing expendable rocket stage. This vehicle, termed StarBooster, will be the first stage of a family of launch vehicles. By combining these elements, we believe we can reduce the cost and risk of fielding a new partially reusable launch system. This report summarizes the work performed on the StarBooster concept since the company's inception in 1996. Detailed analyses are on-going and future reports will focus on the maturation of the vehicle and system design.

KSC-06pd1284

NASA Image and Video Library

2006-06-28

KENNEDY SPACE CENTER, FLA. - At the Cape Canaveral forecast facility in Florida, Shuttle Weather Officer Kathy Winters briefs the media on how the launch weather forecast is developed. Attendees also were able to meet the forecasters for the space shuttle and the expendable launch vehicles. Also participating were members of the Applied Meteorology Unit who provide special expertise to the forecasters by analyzing and interpreting unusual or inconsistent weather data. The media were able to see the release of the Rawinsonde weather balloon carrying instruments aloft to be used as part of developing the forecast. Photo credit: NASA/George Shelton

Russian Soyuz Moves to Launch Pad

NASA Technical Reports Server (NTRS)

2000-01-01

The Soyuz TM-31 launch vehicle, which carried the first resident crew to the International Space Station, moves toward the launch pad at the Baikonur complex in Kazakhstan. The Russian Soyuz launch vehicle is an expendable spacecraft that evolved out of the original Class A (Sputnik). From the early 1960' until today, the Soyuz launch vehicle has been the backbone of Russia's marned and unmanned space launch fleet. Today, the Soyuz launch vehicle is marketed internationally by a joint Russian/French consortium called STARSEM. As of August 2001, there have been ten Soyuz missions under the STARSEM banner.

KSC-02pd1949

NASA Image and Video Library

2002-12-17

KENNEDY SPACE CENTER, FLA. -- Workers at the Cape Canaveral Air Force Station Skid Strip get ready to remove the Pegasus XL Expendable Launch Vehicle attached underneath the Orbital Sciences L-1011 aircraft. The Pegasus will be transported to the Multi-Payload Processing Facility for testing and verification. The Pegasus will undergo three flight simulations prior to its scheduled launch in late January 2003. The Pegasus XL will carry NASA's Solar Radiation and Climate Experiment (SORCE) into orbit. Built by Orbital Sciences Space Systems Group, SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere. .

Regenerable non-venting thermal control subsystem for extravehicular activity

NASA Technical Reports Server (NTRS)

Roebelen, George J.; Bayes, Stephen A.; Lawson, B. Mike

1986-01-01

Routine and complex EVAs call for more effective heat rejection systems in order to maximize mission productivity; an optimum EVA mobility unit (EMU) thermal control subsystem must require no expendables and introduce no contaminants into the environment, while conforming to minimum size limits and allowing easy regeneration. Attention is presently given to two thermal control subsystems, one of which can be integrated with the existing Space Shuttle Orbiter EMU to provide a 3-hour nonventing heat rejection capability, while the other can furnish the entire heat rejection capability requirement for an 8-hour Space Station EVA.

Thermodynamic Improvements for the Space Thermoacoustic Refrigerator (STAR)

DTIC Science & Technology

1988-06-01

Sondhauss proved that the vibration of the glass itself did not generate the sound, but he offered no explanation as to what did. In his description...noise of aeroengines above that predicted by theory. He determined that the sound was produced by unsteady heat transfer. Each of these latter three...lifetimes (expendable cryogens) and high vibration levels and low reliability (closed cycle refrigerators). The advantages of the thermoacoustic

Apollo 7/S-IVB Rendezvous in space

NASA Image and Video Library

1968-10-11

AS07-03-1538 (11 Oct. 1968) --- The expended Saturn IVB stage as photographed from the Apollo 7 spacecraft during transposition and docking maneuvers. This photograph was taken during Apollo 7's second revolution of Earth. Earth below has heavy cloud cover. The round, white disc inside the open panels of the Saturn IVB is a simulated docking target similar to that used on the lunar module for docking during lunar missions.

Apollo 7/S-IVB Rendezvous in space

NASA Image and Video Library

1968-10-11

AS07-03-1531 (11 Oct. 1968) --- The expended Saturn IVB stage as photographed from the Apollo 7 spacecraft during transposition and docking maneuvers. This photograph was taken over Sonora, Mexico, during Apollo 7's second revolution of Earth. The round, white disc inside the open panels of the Saturn IVB is a simulated docking target similar to that used on the lunar module for docking during lunar missions.

Robotic Waterblasting

NASA Technical Reports Server (NTRS)

2004-01-01

The Waterblast Research Cell supports development of automated systems that remove thermal protection materials and coatings from space flight hardware. These systems remove expended coatings without harsh chemicals or damaging underlying material. Potential applications of this technology include the removal of coatings from industrial machinery, aircraft, and other large structures. Use of the robot improves worker safety by reducing the exposure of persornel to high-pressure water. This technology is a proactive alternative to hazardous chemical strippers.

Artist's Concept of Propulsive Small Expendable Deployer System (ProSEDS)

NASA Technical Reports Server (NTRS)

1999-01-01

Pictured is an artist's concept of NASA's Propulsive Small Expendable Deployer System experiment (ProSEDS). ProSEDS will demonstrate the use of an electrodynamic tether, basically a long, thin wire, for propulsion. An electrodynamic tether uses the same principles as electric motors in toys, appliances and computer disk drives, and generators in automobiles and power plants. When electrical current is flowing through the tether, a magnetic field is produced that pushes against the magnetic field of the Earth. For ProSEDS, the current in the tether results by virtue of the voltage generated when the tether moves through the Earth's magnetic field at more than 17,000 mph. This approach can produce drag thrust generating useable power. Since electrodynamic tethers require no propellant, they could substantially reduce the weight of the spacecraft and provide a cost-effective method of reboosting spacecraft. The initial flight of ProSEDS is scheduled to fly aboard an Air Force Delta II rocket in summer of 2002. In orbit, ProSEDS will deploy from a Delta II second stage. It will be a 3.1-mile (5 kilometer) long, ultrathin base-wire tether cornected with a 6.2-mile (10 kilometer) long nonconducting tether. The ProSEDS experiment is managed by the Space Transportation Directorate at the Marshall Space Flight Center.

KSC-01pp1469

NASA Image and Video Library

2001-08-10

KENNEDY SPACE CENTER, Fla. -- The solid rocket booster on Space Shuttle Discovery expends a column of flame as it hurtles into the sky on mission STS-105 to the International Space Station. Liftoff from Launch Pad 39A occurred at 5:10:14 p.m. EDT. Besides the Shuttle crew of four, Discovery carries the Expedition Three crew who will replace Expedition Two on the Space Station. The mission includes the third flight of an Italian-built Multi-Purpose Logistics Module delivering additional scientific racks, equipment and supplies for the Space Station and the Early Ammonia Servicer (EAS) tank. The EAS, which will be attached to the Station during two spacewalks, contains spare ammonia for the Station’s cooling system. The three-member Expedition Two crew will be returning to Earth aboard Discovery after a five-month stay on the Station

KSC-02pp1641

NASA Image and Video Library

2002-10-18

KENNEDY SPACE CENTER, FLA. -- Workers supervise the move of the suspended TDRS-J spacecraft towards a workstand in the Spacecraft Assembly and Encapsulation Facility-2 (SAEF-2) for final checkout and processing before launch, currently targeted for Nov. 20. TDRS-J is the third in the current series of three Tracking and Data Relay Satellites designed to replenish the existing on-orbit fleet of six spacecraft, the first of which was launched in 1983. The Tracking and Data Relay Satellite System is the primary source of space-to-ground voice, data and telemetry for the Space Shuttle. It also provides communications with the International Space Station and scientific spacecraft in low-earth orbit, such as the Hubble Space Telescope, and launch support for some expendable vehicles. This new advanced series of satellites will extend the availability of TDRS communications services until approximately 2017.

KSC-02pp1643

NASA Image and Video Library

2002-10-18

KENNEDY SPACE CENTER, FLA. -- Workers supervise the placement of the TDRS-J spacecraft onto a workstand in the Spacecraft Assembly and Encapsulation Facility-2 (SAEF-2) for final checkout and processing before launch, currently targeted for Nov. 20. TDRS-J is the third in the current series of three Tracking and Data Relay Satellites designed to replenish the existing on-orbit fleet of six spacecraft, the first of which was launched in 1983. The Tracking and Data Relay Satellite System is the primary source of space-to-ground voice, data and telemetry for the Space Shuttle. It also provides communications with the International Space Station and scientific spacecraft in low-earth orbit, such as the Hubble Space Telescope, and launch support for some expendable vehicles. This new advanced series of satellites will extend the availability of TDRS communications services until approximately 2017.

KSC-02pd1576

NASA Image and Video Library

2002-10-18

KENNEDY SPACE CENTER, FLA. - At the KSC Shuttle Landing Facility, an overhead crane lifts the container with the TDRS-J spacecraft onto a transport vehicle. In the background is the Air Force C-17 air cargo plane that delivered it. TDRS-J is the third in the current series of three Tracking and Data Relay Satellites designed to replenish the existing on-orbit fleet of six spacecraft, the first of which was launched in 1983. The Tracking and Data Relay Satellite System is the primary source of space-to-ground voice, data and telemetry for the Space Shuttle. It also provides communications with the International Space Station and scientific spacecraft in low-earth orbit such as the Hubble Space Telescope, and launch support for some expendable vehicles. This new advanced series of satellites will extend the availability of TDRS communications services until approximately 2017.

KSC-02pd1575

NASA Image and Video Library

2002-10-18

KENNEDY SPACE CENTER, FLA. - Workers attach the container with the TDRS-J spacecraft inside to an overhead crane. The container will be placed on a transporter and taken to the Spacecraft Assembly and Encapsulation Facility-2 (SAEF-2). TDRS-J is the third in the current series of three Tracking and Data Relay Satellites designed to replenish the existing on-orbit fleet of six spacecraft, the first of which was launched in 1983. The Tracking and Data Relay Satellite System is the primary source of space-to-ground voice, data and telemetry for the Space Shuttle. It also provides communications with the International Space Station and scientific spacecraft in low-earth orbit such as the Hubble Space Telescope, and launch support for some expendable vehicles. This new advanced series of satellites will extend the availability of TDRS communications services until approximately 2017.

Affordable In-Space Transportation

NASA Technical Reports Server (NTRS)

Curtis, L. A.; VanDyke, M. K.; Lajoie, R. M.; Woodcock, G. R.

1996-01-01

Current and proposed launch systems will provide access to low-Earth orbit (LEO), and destinations beyond LEO, but the cost of delivering payloads will preclude the use of these services by many users. To develop and encourage revolutionary commercial utilization of geosynchronous orbit (GEO) and to provide an affordable means to continue NASA space science and exploration missions, the transportation costs to in-space destinations must be reduced. The principal objective of this study was to conceptually define three to four promising approaches to in-space transportation for delivery of satellites and other payloads, 3,000- to 10,000-lb class, to GEO destinations. This study established a methodology for evaluating in-space transportation systems based on life-cycle cost. The reusable concepts seemed to fare better in the evaluation than expendable, since a major driver in the life-cycle cost was the stage production cost.

A multilevel control approach for a modular structured space platform

NASA Technical Reports Server (NTRS)

Chichester, F. D.; Borelli, M. T.

1981-01-01

A three axis mathematical representation of a modular assembled space platform consisting of interconnected discrete masses, including a deployable truss module, was derived for digital computer simulation. The platform attitude control system as developed to provide multilevel control utilizing the Gauss-Seidel second level formulation along with an extended form of linear quadratic regulator techniques. The objectives of the multilevel control are to decouple the space platform's spatial axes and to accommodate the modification of the platform's configuration for each of the decoupled axes.

Space Science

NASA Image and Video Library

2000-11-01

In this photograph, the composite material mirror is tested in the X-Ray Calibration Facility at the Marshall Space Flight Center for the James Webb Space Telescope (JWST). The mirror test conducted was to check the ability to accurately model and predict the cryogenic performance of complex mirror systems, and the characterization of cryogenic dampening properties of beryllium. The JWST, a next generation successor to the Hubble Space Telescope (HST), was named in honor of James W. Webb, NASA's second administrator, who led NASA in the early days of the fledgling Aerospace Agency. Scheduled for launch in 2010 aboard an expendable launch vehicle, the JWST will be able to look deeper into the universe than the HST because of the increased light-collecting power of its larger mirror and the extraordinary sensitivity of its instrument to infrared light.

Technology for the future - Long range planning for space technology development

NASA Technical Reports Server (NTRS)

Collier, Lisa D.; Breckenridge, Roger A.; Llewellyn, Charles P.

1992-01-01

NASA's Office of Aeronautics and Space Technology (OAST) has begun the definition of an Integrated Technology Plan for the civilian space program which guides long-term technology development for space platforms, in light of continuing marker research and other planning data. OAST has conferred particular responsibility for future candidate space mission evaluations and platform performance requirement projections to NASA-Langley. An implementation plan is devised which is amenable to periodic space-platform technology updates.

KSC-98pc1182

NASA Image and Video Library

1998-09-29

KENNEDY SPACE CENTER, FLA. -- In the Payload Hazardous Servicing Facility, workers complete the insulation of Deep Space 1. The first flight in NASA's New Millennium Program, Deep Space 1 is designed to validate 12 new technologies for scientific space missions of the next century. Onboard experiments include an ion propulsion engine and software that tracks celestial bodies so the spacecraft can make its own navigation decisions without the intervention of ground controllers. Deep Space 1 will complete most of its mission objectives within the first two months, but may also do a flyby of a near-Earth asteroid, 1992 KD, in July 1999. Deep Space 1 will be launched aboard a Boeing Delta 7326 rocket from Launch Pad 17A, Cape Canaveral Air Station, in October. Delta II rockets are medium capacity expendable launch vehicles derived from the Delta family of rockets built and launched since 1960. Since then there have been more than 245 Delta launches

KSC-98pc1157

NASA Image and Video Library

1998-09-22

KENNEDY SPACE CENTER, FLA. -- Workers in the Payload Hazardous Servicing Facility maneuver a second solar panel to attach it to Deep Space 1. The first flight in NASA's New Millennium Program, Deep Space 1 is designed to validate 12 new technologies for scientific space missions of the next century. Onboard experiments include an ion propulsion engine and software that tracks celestial bodies so the spacecraft can make its own navigation decisions without the intervention of ground controllers. Deep Space 1 will complete most of its mission objectives within the first two months, but may also do a flyby of a near-Earth asteroid, 1992 KD, in July 1999. Deep Space 1 will be launched aboard a Boeing Delta 7326 rocket from Launch Pad 17A, Cape Canaveral Air Station, in October. Delta II rockets are medium capacity expendable launch vehicles derived from the Delta family of rockets built and launched since 1960. Since then there have been more than 245 Delta launches

KSC-98pc1178

NASA Image and Video Library

1998-09-29

KENNEDY SPACE CENTER, FLA. -- In the Payload Hazardous Servicing Facility, KSC workers place insulating blankets on Deep Space 1 to prepare it for launch. The first flight in NASA's New Millennium Program, Deep Space 1 is designed to validate 12 new technologies for scientific space missions of the next century. Onboard experiments include an ion propulsion engine and software that tracks celestial bodies so the spacecraft can make its own navigation decisions without the intervention of ground controllers. Deep Space 1 will complete most of its mission objectives within the first two months, but may also do a flyby of a near-Earth asteroid, 1992 KD, in July 1999. Deep Space 1 will be launched aboard a Boeing Delta 7326 rocket from Launch Pad 17A, Cape Canaveral Air Station, in October. Delta II rockets are medium capacity expendable launch vehicles derived from the Delta family of rockets built and launched since 1960. Since then there have been more than 245 Delta launches

KSC-98pc1175

NASA Image and Video Library

1998-09-29

KENNEDY SPACE CENTER, FLA. -- Workers in the Payload Hazardous Servicing Facility install blanket insulation on Deep Space 1. The first flight in NASA's New Millennium Program, Deep Space 1 is designed to validate 12 new technologies for scientific space missions of the next century. Onboard experiments include an ion propulsion engine and software that tracks celestial bodies so the spacecraft can make its own navigation decisions without the intervention of ground controllers. Deep Space 1 will complete most of its mission objectives within the first two months, but may also do a flyby of a near-Earth asteroid, 1992 KD, in July 1999. Deep Space 1 will be launched aboard a Boeing Delta 7326 rocket from Launch Pad 17A, Cape Canaveral Air Station, in October. Delta II rockets are medium capacity expendable launch vehicles derived from the Delta family of rockets built and launched since 1960. Since then there have been more than 245 Delta launches

KSC-98pc1158

NASA Image and Video Library

1998-09-29

KENNEDY SPACE CENTER, FLA. -- Workers in the Payload Hazardous Servicing Facility get ready to attach a second solar panel to Deep Space 1. The first flight in NASA's New Millennium Program, Deep Space 1 is designed to validate 12 new technologies for scientific space missions of the next century. Onboard experiments include an ion propulsion engine and software that tracks celestial bodies so the spacecraft can make its own navigation decisions without the intervention of ground controllers. Deep Space 1 will complete most of its mission objectives within the first two months, but will also do a flyby of a near-Earth asteroid, 1992 KD, in July 1999. Deep Space 1 will be launched aboard a Boeing Delta II rocket from Launch Pad 17A, Cape Canaveral Air Station, in October. Delta II rockets are medium capacity expendable launch vehicles derived from the Delta family of rockets built and launched since 1960. Since then there have been more than 245 Delta launches

KSC-98pc1174

NASA Image and Video Library

1998-09-29

KENNEDY SPACE CENTER, FLA. -- Workers in the Payload Hazardous Servicing Facility begin installing blanket insulation on Deep Space 1. The first flight in NASA's New Millennium Program, Deep Space 1 is designed to validate 12 new technologies for scientific space missions of the next century. Onboard experiments include an ion propulsion engine and software that tracks celestial bodies so the spacecraft can make its own navigation decisions without the intervention of ground controllers. Deep Space 1 will complete most of its mission objectives within the first two months, but may also do a flyby of a near-Earth asteroid, 1992 KD, in July 1999. Deep Space 1 will be launched aboard a Boeing Delta 7326 rocket from Launch Pad 17A, Cape Canaveral Air Station, in October. Delta II rockets are medium capacity expendable launch vehicles derived from the Delta family of rockets built and launched since 1960. Since then there have been more than 245 Delta launches

KSC-98pc1176

NASA Image and Video Library

1998-09-29

KENNEDY SPACE CENTER, FLA. -- Workers in the Payload Hazardous Servicing Facility finish installing blanket insulation on Deep Space 1. The first flight in NASA's New Millennium Program, Deep Space 1 is designed to validate 12 new technologies for scientific space missions of the next century. Onboard experiments include an ion propulsion engine and software that tracks celestial bodies so the spacecraft can make its own navigation decisions without the intervention of ground controllers. Deep Space 1 will complete most of its mission objectives within the first two months, but may also do a flyby of a near-Earth asteroid, 1992 KD, in July 1999. Deep Space 1 will be launched aboard a Boeing Delta 7326 rocket from Launch Pad 17A, Cape Canaveral Air Station, in October. Delta II rockets are medium capacity expendable launch vehicles derived from the Delta family of rockets built and launched since 1960. Since then there have been more than 245 Delta launches

Recognition unit-free and self-cleaning photoelectrochemical sensing platform on TiO2 nanotube photonic crystals for sensitive and selective detection of dopamine release from mouse brain.

PubMed

Xin, Yanmei; Li, Zhenzhen; Wu, Wenlong; Fu, Baihe; Wu, Hongjun; Zhang, Zhonghai

2017-01-15

For implementing sensitive and selective detection of biological molecules, the biosensors are been designed more and more complicated. The exploration of detection platform in a simple way without loss their sensitivity and selectivity is always a big challenge. Herein, a prototype of recognition biomolecule unit-free photoelectrochemical (PEC) sensing platform with self-cleaning activity is proposed with TiO 2 nanotube photonic crystal (TiO 2 NTPCs) materials as photoelectrode, and dopamine (DA) molecule as both sensitizer and target analyte. The unique adsorption between DA and TiO 2 NTPCs induces the formation of charge transfer complex, which not only expends the optical absorption of TiO 2 into visible light region, thus significantly boosts the PEC performance under illumination of visible light, but also implements the selective detection of DA on TiO 2 photoelectrode. This simple but efficient PEC analysis platform presents a low detection limit of 0.15nm for detection of DA, which allows to realize the sensitive and selective determination of DA release from the mouse brain for its practical application after coupled with a microdialysis probe. The DA functionalized TiO 2 NTPCs PEC sensing platform opens up a new PEC detection model, without using extra-biomolecule auxiliary, just with target molecule naturally adsorbed on the electrode for sensitive and selective detection, and paves a new avenue for biosensors design with minimalism idea. Copyright © 2016 Elsevier B.V. All rights reserved.

TDRS-L Tribute Decal to Arthur "Skip" Mackey, Jr.

NASA Image and Video Library

2014-01-22

CAPE CANAVERAL, Fla. – This memorial message was added to the Atlas V rocket for NASA's Tracking and Data Relay Satellite, or TDRS-L, spacecraft being prepared for launch from Cape Canaveral Air Force Station's Launch Complex 41. Arthur J. "Skip" Mackey Jr. was the “Voice of NASA” during the 1960s, 1970s and early 1980s for flight commentary after liftoff for expendable vehicles launched from Cape Canaveral. Mackey served as branch chief for Telemetry and Communications at Hangar AE in the agency’s Expendable Launch Vehicle Program and then the Launch Services Program for 39 years. He died in Fort Lauderdale, Fla., on Nov. 19, 2013. The TDRS-L spacecraft is the second of three new satellites designed to ensure vital operational continuity for NASA by expanding the lifespan of the Tracking and Data Relay Satellite System TDRSS fleet, which consists of eight satellites in geosynchronous orbit. The spacecraft provide tracking, telemetry, command and high bandwidth data return services for numerous science and human exploration missions orbiting Earth. These include NASA's Hubble Space Telescope and the International Space Station. TDRS-L has a high-performance solar panel designed for more spacecraft power to meet the growing S-band communications requirements. TDRSS is one of NASA Space Communication and Navigation’s SCaN three networks providing space communications to NASA’s missions. For more information more about TDRS-L, visit: http://www.nasa.gov/tdrs To learn more about SCaN, visit: www.nasa.gov/scan For more on "Skip" Mackey go to: http://www.nasa.gov/content/skip-mackey-remembered-by-colleagues-as-voice-of-nasa/ Image credit: United Launch Alliance

Regional convergence platforms in Europe—Innovation for space through technology partnerships

NASA Astrophysics Data System (ADS)

Bütfering, Peter

2010-05-01

Upcoming European and national space exploration programs and projects require new capabilities and scientific-technological solutions, and therefore external contributions to innovation. On the other hand European core (industrial) regions are searching of partners for innovation to strengthen their regional economy. In this context the German-based company European Space Innovation AG (former Adam Alva Neil)—highly experienced in the area of convergence activities between space and other sectors—has developed the model of regional convergence platforms (named 'SpaceInnovation'). These platforms are designed to foster technology partnerships between regional companies and institutes from 'non-space' and the space sector (agencies/industry). The article reflects this regional approach and shows examples in three different directions: SpaceInnovation Saar, an benchmark convergence platform initiated by the Saarland region. SpaceInnovation Europe, an European regions network approach. European SpaceInnovation Agent, an interface approach for systematic and sustainable convergence activities.

Advanced Extravehicular Protective System (AEPS) study

NASA Technical Reports Server (NTRS)

Williams, J. L.; Webbon, B. W.; Copeland, R. J.

1972-01-01

A summary is presented of Advanced Extravehicular Protective Systems (AEPS) for the future missions beyond Skylab in earth orbit, on the lunar surface, and on the Martian surface. The study concentrated on the origination of regenerable life support concepts for use in portable extravehicular protective systems, and included evaluation and comparison with expendable systems, and selection of life support subsystems. The study was conducted in two phases. In the first phase, subsystem concepts for performing life support functions in AEPS which are regenerable or partially regenerable were originated, and in addition, expendable subsystems were considered. Parametric data for each subsystem concept were evolved including subsystem weight and volume, power requirement, thermal control requirement; base regeneration equipment weight and volume, requirement. The second phase involved an evaluation of the impact of safety considerations involving redundant and/or backup systems on the selection of the regenerable life support subsystems. In addition, the impact of the space shuttle program on regenerable life support subsystem development was investigated.

Performance estimates for space shuttle vehicles using a hydrogen or a methane fueled turboramjet powered first stage

NASA Technical Reports Server (NTRS)

Knip, G., Jr.; Eisenberg, J. D.

1972-01-01

Two- and three-stage (second stage expendable) shuttle vehicles, both having a hydrogen-fueled, turboramjet-powered first stage, are compared with a two-stage, VTOHL, all-rocket shuttle in terms of payload fraction, inert weight, development cost, operating cost, and total cost. All of the vehicles place 22,680 kilograms of payload into a 500-kilometer orbit. The upper stage(s) uses hydrogen-oxygen rockets. The effect on payload fraction and vehicle inert weight of methane and methane-FLOX as a fuel-propellant combination for the three-stage vehicle is indicated. Compared with a rocket first stage for a two-stage shuttle, an airbreathing first stage results in a higher payload fraction and a lower operating cost, but a higher total cost. The effect on cost of program size and first-stage flyback is indicated. The addition of an expendable rocket second stage (three-stage vehicle) improves the payload fraction but is unattractive economically.

Automated Platform Management System Scheduling

NASA Technical Reports Server (NTRS)

Hull, Larry G.

1990-01-01

The Platform Management System was established to coordinate the operation of platform systems and instruments. The management functions are split between ground and space components. Since platforms are to be out of contact with the ground more than the manned base, the on-board functions are required to be more autonomous than those of the manned base. Under this concept, automated replanning and rescheduling, including on-board real-time schedule maintenance and schedule repair, are required to effectively and efficiently meet Space Station Freedom mission goals. In a FY88 study, we developed several promising alternatives for automated platform planning and scheduling. We recommended both a specific alternative and a phased approach to automated platform resource scheduling. Our recommended alternative was based upon use of exactly the same scheduling engine in both ground and space components of the platform management system. Our phased approach recommendation was based upon evolutionary development of the platform. In the past year, we developed platform scheduler requirements and implemented a rapid prototype of a baseline platform scheduler. Presently we are rehosting this platform scheduler rapid prototype and integrating the scheduler prototype into two Goddard Space Flight Center testbeds, as the ground scheduler in the Scheduling Concepts, Architectures, and Networks Testbed and as the on-board scheduler in the Platform Management System Testbed. Using these testbeds, we will investigate rescheduling issues, evaluate operational performance and enhance the platform scheduler prototype to demonstrate our evolutionary approach to automated platform scheduling. The work described in this paper was performed prior to Space Station Freedom rephasing, transfer of platform responsibility to Code E, and other recently discussed changes. We neither speculate on these changes nor attempt to predict the impact of the final decisions. As a consequence some of our work and results may be outdated when this paper is published.

New Generation Flask Sampling Technology Final Report

DOE Office of Scientific and Technical Information (OSTI.GOV)

Smith, James R.

Scientists are turning their focus to the Arctic, site of one of the strongest climate change signals. A new generation of technologies is required to function within that harsh environment, chart evolution of its trace gases and provide new kinds of information for models of the atmosphere. Our response to the solicitation tracks how global atmospheric monitoring was launched more than a half century ago; namely, acquisition of discrete samples of air by flask and subsequent analysis in the laboratory. AOS is proposing to develop a new generation of flask sampling technology. It will enable the new Arctic programs tomore » begin with objective high density sampling of the atmosphere by UAS. The Phase I program will build the prototype flask technology and show that it can acquire and store mol fractions of CH4 and CO2 and value of δ13C with good fidelity. A CAD model will be produced for the entire platform including a package with 100 flasks and the airframe with auto-pilot, electronic propulsion and ground-to-air communications. A mobile flask analysis station will be prototyped in Phase I and designed to final form in Phase II. It expends very small sample per analysis and will interface directly to the flask package integrated permanently into the UAS fuselage. Commercial Applications and Other Benefits: • The New Generation Flask Sampling Technology able to provide a hundred or more samples of air per UAS mission. • A mobile analysis station expending far less sample than the existing ones and small enough to be stationed at the remote sites of Arctic operations. • A new form of validation for continuous trace gas observations from all platforms including the small UAS. • Further demonstration to potential customers of the AOS capabilities to invent, build, deploy and exploit entire platforms for observations of Earth’s atmosphere and ocean. Key Words: Flask Sampler, Mobile Analysis Station, Trace Gas, CO2, CH4, δC13, UAS, Baseline Airborne Observatory, Arctic, Climate Change. Summary for Members of Congress: The air, land and sea of the Arctic combine to produce a large climate change signal. AOS is proposing to develop unmanned airborne technologies able to begin prompt, objective observations of the signal’s atmospheric component.« less

7 CFR 3019.35 - Supplies and other expendable property.

Code of Federal Regulations, 2010 CFR

2010-01-01

... of unused supplies exceeding $5000 in total aggregate value upon termination or completion of the... 7 Agriculture 15 2010-01-01 2010-01-01 false Supplies and other expendable property. 3019.35... Requirements Property Standards § 3019.35 Supplies and other expendable property. (a) Title to supplies and...

Benefit from NASA

NASA Image and Video Library

2004-04-15

The Waterblast Research Cell supports development of automated systems that remove thermal protection materials and coatings from space flight hardware. These systems remove expended coatings without harsh chemicals or damaging underlying material. Potential applications of this technology include the removal of coatings from industrial machinery, aircraft, and other large structures. Use of the robot improves worker safety by reducing the exposure of persornel to high-pressure water. This technology is a proactive alternative to hazardous chemical strippers.

The Army Needs to Recoup Funds Expended on Property Damaged in an Accident at a Development Subcontractor’s Facility (Redacted)

DTIC Science & Technology

2012-05-24

liability for the JLENS prope1iy damaged in an accident at a subcontractor’s facility. The accident occmTed when high winds caused an Airship ...modernization proponent for space, high - altitude and global missile defense, is the Almy operational integrator for global missile defense, and conducts...Alexandria, VA 22350-1500 Acronyms and Abbreviations AMS Airship Management Services DCMA Defense Contract

Noise Transmission Studies of an Advanced Grid-Stiffened Composite Fairing

DTIC Science & Technology

2007-10-01

increase in blanket thickness and weight [7]. The evolved expendable launch vehicle (EELV) programs have conducted research to ensure that their launch...uses an aluminum fairing that is 4 to 5 m in diameter. The Atlas V 500 and heavy lift vehicles use a fairing designed and built by Contraves , which...builds the Ariane V launch vehicle for the European Space Agency. Contraves developed an innovative acoustic blanket for fairing noise reduction that

In-space fabrication of thin-film structures

NASA Technical Reports Server (NTRS)

Lippman, M. E.

1972-01-01

A conceptual study of physical vapor-deposition processes for in-space fabrication of thin-film structures is presented. Potential advantages of in-space fabrication are improved structural integrity and surface reflectivity of free-standing ultra-thin films and coatings. Free-standing thin-film structures can find use as photon propulsion devices (solar sails). Other applications of the concept involve free-standing shadow shields, or thermal control coatings of spacecraft surfaces. Use of expendables (such as booster and interstage structures) as source material for the physical vapor deposition process is considered. The practicability of producing thin, textured, aluminum films by physical vapor deposition and subsequent separation from a revolving substrate is demonstrated by laboratory experiments. Heating power requirement for the evaporation process is estimated for a specific mission.

Psycho-social training for man in space

NASA Astrophysics Data System (ADS)

Kass, R.; Kass, J. R.

1999-11-01

In preparation for the international manned space station various international and national space agencies are already participating with the Russian MIR programme with short, medium, and long term presence on the MIR station. Although selection criteria for all crew include careful psychological screening, with some effort also regarding team build-up, this has proved insufficient; moreover, little or no effort is expended in the area of psycho-social- or team training. This paper propounds the authors' thesis that, in addition to the steps already being taken, psycho-social training is essential for long-duration flight. A concrete proposal is made for such a training program, with an overview of how such a program will look like; examples of past applications are given.

KSC-02pd2017

NASA Image and Video Library

2002-12-18

KENNEDY SPACE CENTER, FLA. -- Workers in clean room attire supervise the delivery of a Pegasus XL Expendable Launch Vehicle to the Multi-Purpose Payload Facility (MPPF). Next, it will be moved into a highbay where it will undergo testing, verification, and three flight simulations prior to its scheduled launch. The vehicle, nestled beneath an Orbital Sciences L-1011 aircraft, arrived at the Cape Canaveral Air Force Station Skid Strip on Dec. 17. It is commissioned to carry NASA's Solar Radiation and Climate Experiment (SORCE) spacecraft into orbit in late January 2003. Built by Orbital Sciences Space Systems Group, SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere with four instruments built by the University of Colorado's Laboratory for Atmospheric and Space Physics (LASP).

Explorer Program: X-ray Timing Explorer

NASA Technical Reports Server (NTRS)

1995-01-01

This booklet describes the X-ray Timing Explorer (XTE), one in a series of Explorer missions administered by the National Aeronautics and Space Administration's (NASA) Office of Space Science and managed by the NASA Goddard Space Flight Center (GSFC). The X-ray astronomy observatory is scheduled for launch into low-Earth orbit by Delta 2 expendable launch vehicle in late summer of 1995. The mission is expected to operate for at least 2 years and will carry out in-depth timing and spectral studies of the X-ray sources in the 2 to 200 kilo-electron Volt (keV) range. XTE is intended to study the temporal and broad-band spectral phenomena associated with stellar and galactic systems containing compact objects, including neutron stars, white dwarfs, and black holes.

KSC-02pd2019

NASA Image and Video Library

2002-12-18

KENNEDY SPACE CENTER, FLA. -- A Pegasus XL Expendable Launch Vehicle sits atop a transporter following its arrival in the Multi-Purpose Payload Facility (MPPF). Next, it will be moved into a highbay where it will undergo testing, verification, and three flight simulations prior to its scheduled launch. The vehicle, nestled beneath an Orbital Sciences L-1011 aircraft, arrived at the Cape Canaveral Air Force Station Skid Strip on Dec. 17. It is commissioned to carry NASA's Solar Radiation and Climate Experiment (SORCE) spacecraft into orbit in late January 2003. Built by Orbital Sciences Space Systems Group, SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere with instruments built by the University of Colorado's Laboratory for Atmospheric and Space Physics (LASP).

KSC-02pd2020

NASA Image and Video Library

2002-12-18

KENNEDY SPACE CENTER, FLA. -- A Pegasus XL Expendable Launch Vehicle sits atop a transporter following its arrival in the Multi-Purpose Payload Facility (MPPF). Next, it will be moved into a highbay where it will undergo testing, verification, and three flight simulations prior to its scheduled launch. The vehicle, nestled beneath an Orbital Sciences L-1011 aircraft, arrived at the Cape Canaveral Air Force Station Skid Strip on Dec. 17. It is commissioned to carry NASA's Solar Radiation and Climate Experiment (SORCE) spacecraft into orbit in late January 2003. Built by Orbital Sciences Space Systems Group, SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere with instruments built by the University of Colorado's Laboratory for Atmospheric and Space Physics (LASP).

Psycho-social training for man in space.

PubMed

Kass, R; Kass, J

1999-07-01

In preparation for the international manned space station various international and national space agencies are already participating with the Russian MIR programme with short, medium, and long term presence on the MIR station. Although selection criteria for all crew include careful psychological screening, with some effort also regarding team build-up, this has proved insufficient; moreover. little or no effort is expended in the area of psycho-social- or team training. This paper propounds the authors' thesis that, in addition to the steps already being taken, psycho-social training is essential for long-duration flight. A concrete proposal is made for such a training program, with an overview of how such a program will look like; examples of past applications are given.

Space research - At a crossroads

NASA Technical Reports Server (NTRS)

Mcdonald, Frank B.

1987-01-01

Efforts which must be expended if U.S. space research is to regain vitality in the next few years are discussed. Small-scale programs are the cornerstone for big science projects, giving both researchers and students a chance to practice the development of space missions and hardware and identify promising goals for larger projects. Small projects can be carried aloft by balloons, sounding rockets, the Shuttle and ELVs. It is recommended that NASA continue the development of remote sensing systems, and join with other government agencies to fund space-based materials science, space biology and medical research. Increased international cooperation in space projects is necessary for affording moderate to large scale missions, for political reasons, and to maximize available space resources. Finally, the establishment and funding of long-range goals in space, particularly the development of the infrastructure and technologies for the exploration and colonization of the planets, must be viewed as the normal outgrowth of the capabilities being developed for LEO operations.

Defensive platform size and survivability. [Platform survivability

DOE Office of Scientific and Technical Information (OSTI.GOV)

Canavan, Gregory H.

1988-06-01

This report discusses the survivability of space platforms, concentrating on space based kinetic energy interceptors. It evaluates the efficacy of hardening, maneuver, self-defense, and deception in extending the survivability of platforms of varying sizes to expected threats, concluding that they should be adequate in the near and mid terms.

Special investigation report: Commercial space launch incident, launch procedure anomaly orbital sciences corporation PEGASUS/SCD-1, 80 nautical miles east of Cape Canaveral, Florida, February 9, 1993

NASA Astrophysics Data System (ADS)

This report explains the procedural anomaly that occurred during the launch sequence of an Orbital Sciences Corporation Pegasus expendable launch vehicle, which was subsequently deployed successfully from an NB-52B airplane, on 9 Feb. 1993. The safety issues discussed in the report include command, control and communications responsibility, launch crew fatigue, launch interphone procedures, efficiency of launch constraints, and the lack of common launch documents. Safety recommendations concerning these issues were made to the Department of Transportation, the National Aeronautics and Space Administration, and the Orbital Sciences Corporation.

Special Investigation Report: Commercial Space Launch Incident, Launch Procedure Anomaly Orbital Sciences Corporation PEGASUS/SCD-1, 80 Nautical Miles East of Cape Canaveral, Florida, February 9, 1993

NASA Technical Reports Server (NTRS)

1993-01-01

This report explains the procedural anomaly that occurred during the launch sequence of an Orbital Sciences Corporation Pegasus expendable launch vehicle, which was subsequently deployed successfully from an NB-52B airplane, on 9 Feb. 1993. The safety issues discussed in the report include command, control and communications responsibility, launch crew fatigue, launch interphone procedures, efficiency of launch constraints, and the lack of common launch documents. Safety recommendations concerning these issues were made to the Department of Transportation, the National Aeronautics and Space Administration, and the Orbital Sciences Corporation.

ProSEDS Telemetry System Utilization of GPS Position Data for Transmitter Cycling

NASA Technical Reports Server (NTRS)

Kennedy, Paul; Sims, Herb

2000-01-01

NASA Marshall Space Flight Center will launch the Propulsive Small Expendable Deployer System (ProSEDS) space experiment in late 2000. ProSEDS will demonstrate the use of an electrodynamic tether propulsion system and will utilize a conducting wire tether to generate limited spacecraft power. This paper will provide an overview of the ProSEDS mission and will discuss the design, development and test of the spacecraft telemetry system which utilizes a custom designed GPS subsystem to determine spacecraft position relative to ground station location and to control transmitter on/off cycling based on spacecraft state vector and ground station visibility.

Life science payloads planning study. [for space shuttle orbiters and spacelab

NASA Technical Reports Server (NTRS)

Nelson, W. G.; Wells, G. W.

1977-01-01

Preferred approaches and procedures were defined for integrating the space shuttle life sciences payload from experiment solicitation through final data dissemination at mission completion. The payloads operations plan was refined and expended to include current information. The NASA-JSC facility accommodations were assessed, and modifications recommended to improve payload processing capability. Standard format worksheets were developed to permit rapid location of experiment requirements and a Spacelab mission handbook was developed to assist potential life sciences investigators at academic, industrial, health research, and NASA centers. Practical, cost effective methods were determined for accommodating various categories of live specimens during all mission phases.

Structural active cooling applications for the Space Shuttle.

NASA Technical Reports Server (NTRS)

Masek, R. V.; Niblock, G. A.; Huneidi, F.

1972-01-01

Analytic and experimental studies have been conducted to evaluate a number of active cooling approaches to structural thermal protection for the Space Shuttle. The primary emphasis was directed toward the thermal protection system. Trade study results are presented for various heat shield material and TPS arrangements. Both metallic and reusable surface insulation (RSI) concepts were considered. Active systems heat sinks consisted of hydrogen, phase change materials, and expendable water. If consideration is given only to controlling the surface temperature, passive TPS was found to provide the most efficient system. Use of active cooling which incorporates some interior temperature control made the thermally less efficient RSI system more attractive.

Recovery of hygiene water by multifiltration. [in space shuttle orbiters

NASA Technical Reports Server (NTRS)

Putnam, David F.; Jolly, Clifford D.; Colombo, Gerald V.; Price, Don

1989-01-01

A multifiltration hygiene water reclamation process that utilizes adsorption and particulate filtration techniques is described and evaluated. The applicability of the process is tested using a simulation of a 4-man subsystem operation for 240 days. It is proposed the process has a 10 year life, weighs 236 kg, and uses 88 kg of expendable filters and adsorption beds to process 8424 kg of water. The data reveal that the multifiltration is an efficient nonphase change technique for hygiene water recovery and that the chemical and microbiological purity of the product water is within the standards specified for the Space Station hygiene water.

System Engineering and Technical Challenges Overcome in the J-2X Rocket Engine Development Project

NASA Technical Reports Server (NTRS)

Ballard, Richard O.

2012-01-01

Beginning in 2006, NASA initiated the J-2X engine development effort to develop an upper stage propulsion system to enable the achievement of the primary objectives of the Constellation program (CxP): provide continued access to the International Space Station following the retirement of the Space Station and return humans to the moon. The J-2X system requirements identified to accomplish this were very challenging and the time expended over the five years following the beginning of the J- 2X effort have been noteworthy in the development of innovations in both the fields for liquid rocket propulsion and system engineering.

KSC-02pd1574

NASA Image and Video Library

2002-10-18

KENNEDY SPACE CENTER, FLA. - A crane is lifted from the SLF to attach to the container with the TDRS-J spacecraft inside (at left). The container will be placed on a transporter and taken to the Spacecraft Assembly and Encapsulation Facility-2 (SAEF-2). TDRS-J is the third in the current series of three Tracking and Data Relay Satellites designed to replenish the existing on-orbit fleet of six spacecraft, the first of which was launched in 1983. The Tracking and Data Relay Satellite System is the primary source of space-to-ground voice, data and telemetry for the Space Shuttle. It also provides communications with the International Space Station and scientific spacecraft in low-earth orbit such as the Hubble Space Telescope, and launch support for some expendable vehicles. This new advanced series of satellites will extend the availability of TDRS communications services until approximately 2017.

43 CFR 12.935 - Supplies and other expendable property.

Code of Federal Regulations, 2010 CFR

2010-10-01

... of unused supplies exceeding $5,000 in total aggregate value upon termination or completion of the... 43 Public Lands: Interior 1 2010-10-01 2010-10-01 false Supplies and other expendable property. 12... Organizations Post-Award Requirements § 12.935 Supplies and other expendable property. (a) Title to supplies and...

29 CFR 99.205 - Basis for determining Federal awards expended.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 29 Labor 1 2010-07-01 2010-07-01 true Basis for determining Federal awards expended. 99.205 Section 99.205 Labor Office of the Secretary of Labor AUDITS OF STATES, LOCAL GOVERNMENTS, AND NON-PROFIT ORGANIZATIONS Audits § 99.205 Basis for determining Federal awards expended. (a) Determining Federal awards...

Processing Depth, Elaboration of Encoding, Memory Stores, and Expended Processing Capacity.

ERIC Educational Resources Information Center

Eysenck, Michael W.; Eysenck, M. Christine

1979-01-01

The effects of several factors on expended processing capacity were measured. Expended processing capacity was greater when information was retrieved from secondary memory than from primary memory, when processing was of a deep, semantic nature than when it was shallow and physical, and when processing was more elaborate. (Author/GDC)

A multimodal micro air vehicle for autonomous flight in near-earth environments

NASA Astrophysics Data System (ADS)

Green, William Edward

Reconnaissance, surveillance, and search-and-rescue missions in near-Earth environments such as caves, forests, and urban areas pose many new challenges to command and control (C2) teams. Of great significance is how to acquire situational awareness when access to the scene is blocked by enemy fire, rubble, or other occlusions. Small bird-sized aerial robots are expendable and can fly over obstacles and through small openings to assist in the acquisition and distribution of intelligence. However, limited flying space and densely populated obstacle fields requires a vehicle that is capable of hovering, but also maneuverable. A secondary flight mode was incorporated into a fixed-wing aircraft to preserve its maneuverability while adding the capability of hovering. An inertial measurement sensor and onboard flight control system were interfaced and used to transition the hybrid prototype from cruise to hover flight and sustain a hover autonomously. Furthermore, the hovering flight mode can be used to maneuver the aircraft through small openings such as doorways. An ultrasonic and infrared sensor suite was designed to follow exterior building walls until an ingress route was detected. Reactive control was then used to traverse the doorway and gather reconnaissance. Entering a dangerous environment to gather intelligence autonomously will provide an invaluable resource to any C2 team. The holistic approach of platform development, sensor suite design, and control serves as the philosophy of this work.

A modular design for rapid-response telecoms and navigation missions

NASA Astrophysics Data System (ADS)

Davies, P.; Liddle, D.; Buckley, John; Sweeting, M.; Roussel-Dupre, Diane; Caffrey, Michael

2004-11-01

Surrey Satellite Technology Ltd and Los Alamos National Laboratory are together building the Cibola Flight Experiment (CFESat), a mission with the aim of flight-proving a reconfigurable processor payload intended for a Low Earth Orbit system. The mission will survey portions of the VHF and UHF radio spectra. The satellite will be launched by the Space Test Program in September 2006 on the USAF Evolved Expendable Launch Vehicle (EELV) using the EELV's Secondary Payload Adapter (ESPA) that allows up to six small satellites to be launched as "piggyback" passengers with larger spacecraft. The payload is based on networks of reprogrammable, Field Programmable Gate Arrays (FPGAs) to process the received signals for ionospheric and lightning studies. The objective is to validate the on-orbit use of commercial, reconfigurable FPGA technology utilizing several different single-event upset mitigation schemes. It will also detect and measure impulsive events that occur in a complex background. SSTL's satellite platform is based on a new, ESPA- compatible, structure housing subsystems and equipments with proven flight heritage from SSTL's disaster monitoring constellation (DMC) and the Topsat mission satellite due for launch in 2005. The structure is mechanically quite complex for a microsatellite having both deployed solar panels and a pair of long booms as part of the payload. The satellite design is highly constrained by the mass and volume requirements of the EELV/EPSA.

Evolutionary space platform concept study. Volume 2, part A: SASP special emphasis trade studies

NASA Technical Reports Server (NTRS)

1982-01-01

Efforts are in progress to define an approach to provide a simple and cost effective solution to the problem of long duration space flight. This approach involves a Space Platform in low Earth orbit, which can be tended by the Space Shuttle and which will provide, for extended periods of time, stability, utilities and access for a variety of replaceable payloads. The feasibility of an evolutionary space system which would cost effectively support unmanned payloads in groups, using a Space Platform which provides centralized basic subsystems is addressed.

[The current state and prospect of Chinese medicine gastroenterology].

PubMed

Zhang, Sheng-Sheng; Zhou, Tao

2012-03-01

The progress and existent problems of Chinese medicine (CM) gastroenterology since the National Eleventh Five-Year Plan were discussed in this article in terms of theory innovation, formulation of clinical pathway and diagnosis-treatment consensus, efficacy assessment, formulation of efficacy assessment scale, advantage diseases, and exploration of the syndrome standardization, progress in science research, academic exchange, and the construction of study platform, and so on. Meanwhile, the development of CM gastroenterology was prospected in the following five aspects: to enhance the theory inheritance and innovation, the construction of discipline standardization; to establish scientific clinical efficacy assessment methods and the standard system; to expend treatment technologies and feature therapies; and to clarify the modern scientific connotation of CM theory and treatment.

Transportation and platforms perspective

NASA Technical Reports Server (NTRS)

Bennett, Gary L.

1992-01-01

The topics covered are presented in viewgraph form and include the following: Office of Aeronautics and Space Technology; space research and technology (R&T); space R&T mission statement; Space R&T program development; R&T strategy; Office of Space Science and Applications (OSSA) technology needs; transportation technology; and space platforms technology.

Accessing space: A catalogue of process, equipment and resources for commercial users

NASA Technical Reports Server (NTRS)

1988-01-01

This catalogue, produced by NASA's Office of Commercial Programs, provides a broad source of information for the commercial developer interested in the areas of microgravity research and remote sensing. Methods for accessing space for research are reviewed including the shuttle, expendable launch vehicles, suborbital sounding rockets, experimental aircraft, and drop towers and other ground-based facilities. Procedures for using these vehicles and facilities are described along with funding options to pay for their use. Experiment apparatus and carriers for microgravity research are also described. A separate directory of resources and services is also included which contains a listing of transportation products and services, a listing of businesses and industries which provide space-related services and products, and a listing of the NASA and CCDS (Center for the Commercial Development of Space) points of contact.

Lunar habitat concept employing the space shuttle external tank.

PubMed

King, C B; Butterfield, A J; Hypes, W D; Nealy, J E; Simonsen, L C

1990-01-01

The space shuttle external tank, which consists of a liquid oxygen tank, an intertank structure, and a liquid hydrogen tank, is an expendable structure used for approximately 8.5 min during each launch. A concept for outfitting the liquid oxygen tank-intertank unit for a 12-person lunar habitat is described. The concept utilizes existing structures and openings for both man and equipment access without compromising the structural integrity of the tank. Living quarters, instrumentation, environmental control and life support, thermal control, and propulsion systems are installed at Space Station Freedom. The unmanned habitat is then transported to low lunar orbit and autonomously soft landed on the lunar surface. Design studies indicate that this concept is feasible by the year 2000 with concurrent development of a space transfer vehicle and manned cargo lander for crew changeover and resupply.

Space Based Intelligence, Surveillance, and Reconnaissance Contribution to Global Strike in 2035

DTIC Science & Technology

2012-02-15

include using high altitude air platforms and airships as a short-term solution, and small satellites with an Operationally Responsive Space (ORS) launch...irreversible threats, along with a worst case scenario. Section IV provides greater detail of the high altitude air platform, airship , and commercial space...Resultantly, the U.S. could use high altitude air platforms, airships , and cyber to complement its space systems in case of denial, degradation, or

Air and Space Power Journal. Volume 19, Number 4, Winter 2005

DTIC Science & Technology

2005-01-01

job-related, two - year undergraduate degree. Open to active duty, ANG, and AFR members, and accredited by the Commission on Colleges of the Southern...amount of funds available each year, Airmen expend very little, if any, of their own money to earn a two -year degree. Education levels throughout...both current and future, is the ap- plication of appropriate effects—controlled and delivered through the air by any means. (See page two of my

Shuttle Derived In-Line Heavy Lift Vehicle

NASA Technical Reports Server (NTRS)

Greenwood, Terry; Twichell, Wallace; Ferrari, Daniel; Kuck, Frederick

2005-01-01

This paper introduces an evolvable Space Shuttle derived family of launch vehicles. It details the steps in the evolution of the vehicle family, noting how the evolving lift capability compares with the evolving lift requirements. A system description is given for each vehicle. The cost of each development stage is described. Also discussed are demonstration programs, the merits of the SSME vs. an expendable rocket engine (RS-68), and finally, the next steps needed to refine this concept.

Expendable launch vehicles technology: A report to the US Senate and the US House of Representatives

NASA Technical Reports Server (NTRS)

1990-01-01

As directed in Public Law 100-657, Commercial Space Launch Act Amendments of 1988, and consistent with National Space Policy, NASA has prepared a report on a potential program of research on technologies to reduce the initial and recurring costs, increase reliability, and improve performance of expendable launch vehicles for the launch of commercial and government spacecraft into orbit. The report was developed in consultation with industry and in recognition of relevant ongoing and planned NASA and DoD technology programs which will provide much of the required launch systems technology for U.S. Government needs. Additional efforts which could be undertaken to strengthen the technology base are identified. To this end, focus is on needs for launch vehicle technology development and, in selected areas, includes verification to permit private-sector new technology application at reduced risk. If such a program were to be implemented, it would entail both government and private-sector effort and resources. The additional efforts identified would augment the existing launch vehicle technology programs. The additional efforts identified have not been funded, based upon agency assessments of relative priority vis-a-vis the existing programs. Throughout the consultation and review process, the industry representatives stressed the overriding importance of continuing the DoD/NASA Advanced Launch Development activity and other government technology programs as a primary source of essential launch vehicle technology.

Expendable launch vehicles technology: A report to the US Senate and the US House of Representatives

NASA Astrophysics Data System (ADS)

1990-07-01

As directed in Public Law 100-657, Commercial Space Launch Act Amendments of 1988, and consistent with National Space Policy, NASA has prepared a report on a potential program of research on technologies to reduce the initial and recurring costs, increase reliability, and improve performance of expendable launch vehicles for the launch of commercial and government spacecraft into orbit. The report was developed in consultation with industry and in recognition of relevant ongoing and planned NASA and DoD technology programs which will provide much of the required launch systems technology for U.S. Government needs. Additional efforts which could be undertaken to strengthen the technology base are identified. To this end, focus is on needs for launch vehicle technology development and, in selected areas, includes verification to permit private-sector new technology application at reduced risk. If such a program were to be implemented, it would entail both government and private-sector effort and resources. The additional efforts identified would augment the existing launch vehicle technology programs. The additional efforts identified have not been funded, based upon agency assessments of relative priority vis-a-vis the existing programs. Throughout the consultation and review process, the industry representatives stressed the overriding importance of continuing the DoD/NASA Advanced Launch Development activity and other government technology programs as a primary source of essential launch vehicle technology.

FASTSAT-HSV01 synergistic observations of the magnetospheric response during active periods: MINI-ME, PISA and TTI

NASA Astrophysics Data System (ADS)

Casas, Joseph; Collier, Michael; Rowland, Douglas; Sigwarth, John; Boudreaux, Mark

Understanding the complex processes within the inner magnetosphere of Earth particularly during storm periods requires coordinated observations of the particle and field environment using both in-situ and remote sensing techniques. In fact in order to gain a better understand-ing of our Heliophysics and potentially improve our space weather forecasting capabilities, new observation mission approaches and new instrument technologies which can provide both cost effective and robust regular observations of magnetospheric activity and other space weather related phenomenon are necessary. As part of the effort to demonstrate new instrument tech-niques and achieve necessary coordinated observation missions, NASA's Fast Affordable Sci-ence and Technology Satellite Huntsville 01 mission (FASTSAT-HSV01) scheduled for launch in 2010 will afford a highly synergistic solution which satisfies payload mission opportunities and launch requirements as well as contributing in the near term to our improved understanding of Heliophysics. NASA's FASTSAT-HSV01 spacecraft on the DoD Space Test Program-S26 (STP-S26) Mission is a multi-payload mission executed by the DoD Space Test Program (STP) at the Space Development and Test Wing (SDTW), Kirtland AFB, NM. and is an example of a responsive and economical breakthrough in providing new possibilities for small space technology-driven and research missions. FASTSAT-HSV is a unique spacecraft platform that can carry multiple small instruments or experiments to low-Earth orbit on a wide range of expendable launch vehicles for a fraction of the cost traditionally required for such missions. The FASTSAT-HSV01 mission allows NASA to mature and transition a technical capability to industry while increasing low-cost access to space for small science and technology (ST) payloads. The FASTSAT-HSV01 payload includes three NASA Goddard Space Flight Center (GSFC) new technology built instruments that will study the terrestrial space environment and potentially contribute to space weather research in a synergistic manner. MINI-ME, a neutral atom imager, will observe the neutral atom inputs to ionospheric heating which can be important during high levels of magnetospheric activity. PISA, a plasma impedance spec-trometer, will measure simultaneously the local electron densities and temperatures as well as measure small scale density structure (500 m spatial scale) during these active periods. TTI, a thermospheric imager, will remotely determine the thermospheric temperature response to this magnetospheric activity. Together, these observations will contribute significantly to a comprehensive understanding of the flow of energy through and the response of the storm-time terrestrial magnetosphere.

FASTSAT-HSV01 Synergistic Observations of the Magnetospheric Response During Active Periods: MINI-ME, PISA and TTI

NASA Technical Reports Server (NTRS)

Casas, Joseph C.; Collier, Michael R.; Rowland, Douglas E.; Sigwarth, John B.; Boudreaux, Mark E.

2010-01-01

Understanding the complex processes within the inner magnetosphere of Earth particularly during storm periods requires coordinated observations of the particle and field environment using both in-situ and remote sensing techniques. In fact in order to gain a better understanding of our Heliophysics and potentially improve our space weather forecasting capabilities, new observation mission approaches and new instrument technologies which can provide both cost effective and robust regular observations of magnetospheric activity and other space weather related phenomenon are necessary. As part of the effort to demonstrate new instrument techniques and achieve necessary coordinated observation missions, NASA's Fast Affordable Science and Technology Satellite Huntsville 01 mission (FASTSAT-HSVOI) scheduled for launch in 2010 will afford a highly synergistic solution which satisfies payload mission opportunities and launch requirements as well as contributing iri the near term to our improved understanding of Heliophysics. NASA's FASTSAT-HSV01 spacecraft on the DoD Space Test Program-S26 (STP-S26) Mission is a multi-payload mission executed by the DoD Space Test Program (STP) at the Space Development and Test Wing (SDTW), Kirtland AFB, NM. and is an example of a responsive and economical breakthrough in providing new possibilities for small space technology-driven and research missions. FASTSAT-HSV is a unique spacecraft platform that can carry multiple small instruments or experiments to low-Earth orbit on a wide range of expendable launch vehicles for a fraction of the cost traditionally required for such missions. The FASTSAT-HSV01 mission allows NASA to mature and transition a technical capability to industry while increasing low-cost access to space for small science and technology (ST) payloads. The FASTSAT-HSV01 payload includes three NASA Goddard Space Flight Center (GSFC) new technology built instruments that will study the terrestrial space environment and potentially contribute to space weather research in a synergistic manner. MINI-ME, a neutral atom imager, will observe the neutral atom inputs to ionospheric heating which can be important during high levels of magnetospheric activity. PISA, a plasma impedance spectrometer, will measure simultaneously the local electron densities and temperatures as well as measure small scale density structure (500 m spatial scale) during these active periods. TTI, a thermospheric imager, will remotely determine the thermospheric temperature response to this magnetospheric activity. Together, these observations will contribute significantly to a comprehensive understanding of the flow of energy through and the response of the storm-time terrestrial magnetosphere.

The 1980 Large space systems technology. Volume 2: Base technology

NASA Technical Reports Server (NTRS)

Kopriver, F., III (Compiler)

1981-01-01

Technology pertinent to large antenna systems, technology related to large space platform systems, and base technology applicable to both antenna and platform systems are discussed. Design studies, structural testing results, and theoretical applications are presented with accompanying validation data. A total systems approach including controls, platforms, and antennas is presented as a cohesive, programmatic plan for large space systems.

45 CFR 264.80 - If a Territory receives Matching Grant funds, what funds must it expend?

Code of Federal Regulations, 2010 CFR

2010-10-01

... funds must it expend? 264.80 Section 264.80 Public Welfare Regulations Relating to Public Welfare OFFICE... Levels of the Territories? § 264.80 If a Territory receives Matching Grant funds, what funds must it expend? (a) If a Territory receives Matching Grant funds under section 1108(b) of the Act, it must: (1...

The Alpha-Helix Concept: Innovative utilization of the Space Station Program. A report to the National Aeronautical and Space Administration requesting establishment of a Sensory Physiology Laboratory on the Space Station

NASA Technical Reports Server (NTRS)

Bandurski, R. S.; Singh, N.

1983-01-01

A major laboratory dedicated to biological-medical research is proposed for the Space Platform. The laboratory would focus on sensor physiology and biochemistry since sensory physiology represents the first impact of the new space environment on living organisms. Microgravity and the high radiation environment of space would be used to help solve the problems of prolonged sojourns in space but, more importantly, to help solve terrestrial problems of human health and agricultural productivity. The emphasis would be on experimental use of microorganisms and small plants and small animals to minimize the space and time required to use the Space Platform for maximum human betterment. The Alpha Helix Concept, that is, the use of the Space Platform to bring experimental biomedicine to a new and extreme frontier is introduced so as to better understand the worldly environment. Staffing and instrumenting the Space Platform biomedical laboratory in a manner patterned after successful terrestrial sensory physiology laboratories is also proposed.

The Alpha-Helix Concept: Innovative utilization of the Space Station Program. A report to the National Aeronautical and Space Administration requesting establishment of a Sensory Physiology Laboratory on the Space Station

NASA Astrophysics Data System (ADS)

Bandurski, R. S.; Singh, N.

1983-10-01

A major laboratory dedicated to biological-medical research is proposed for the Space Platform. The laboratory would focus on sensor physiology and biochemistry since sensory physiology represents the first impact of the new space environment on living organisms. Microgravity and the high radiation environment of space would be used to help solve the problems of prolonged sojourns in space but, more importantly, to help solve terrestrial problems of human health and agricultural productivity. The emphasis would be on experimental use of microorganisms and small plants and small animals to minimize the space and time required to use the Space Platform for maximum human betterment. The Alpha Helix Concept, that is, the use of the Space Platform to bring experimental biomedicine to a new and extreme frontier is introduced so as to better understand the worldly environment. Staffing and instrumenting the Space Platform biomedical laboratory in a manner patterned after successful terrestrial sensory physiology laboratories is also proposed.

United Space Alliance waits to test its one-man submarine for SRB retrieval

NASA Technical Reports Server (NTRS)

2000-01-01

The one-man submarine dubbed DeepWorker 2000 sits on the deck of Liberty Star, one of two KSC solid rocket booster recovery ships. The sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program.

KSC-02pd2014

NASA Image and Video Library

2002-12-18

KENNEDY SPACE CENTER, FLA. -- A Pegasus XL Expendable Launch Vehicle is seen moments after being detached from the underside of an Orbital Sciences L-1011 aircraft and lowered onto a transporter. The aircraft, with the launch vehicle nestled beneath, arrived at the Cape Canaveral Air Force Station Skid Strip on Dec. 17. Next, the vehicle will be towed to the Multi-Purpose Payload Facility (MPPF) where it will undergo testing, verification, and three flight simulations prior to its scheduled launch in late January 2003. It will carry NASA's Solar Radiation and Climate Experiment (SORCE) spacecraft into orbit. Built by Orbital Sciences Space Systems Group, SORCE will study and measure solar irradiance as a source of energy in the Earth's atmosphere with instruments built by the University of Colorado's Laboratory for Atmospheric and Space Physics (LASP).

KSC-98pc1155

NASA Image and Video Library

1998-09-22

KENNEDY SPACE CENTER, FLA. -- Workers in the Payload Hazardous Servicing Facility maneuver a solar panel and rack to be attached to Deep Space 1 (background). The first flight in NASA's New Millennium Program, Deep Space 1 is designed to validate 12 new technologies for scientific space missions of the next century. Onboard experiments include an ion propulsion engine and software that tracks celestial bodies so the spacecraft can make its own navigation decisions without the intervention of ground controllers. Deep Space 1 will complete most of its mission objectives within the first two months, but may also do a flyby of a near-Earth asteroid, 1992 KD, in July 1999. Deep Space 1 will be launched aboard a Boeing Delta 7326 rocket from Launch Pad 17A, Cape Canaveral Air Station, in October. Delta II rockets are medium capacity expendable launch vehicles derived from the Delta family of rockets built and launched since 1960. Since then there have been more than 245 Delta launches

KSC-98pc1156

NASA Image and Video Library

1998-09-22

KENNEDY SPACE CENTER, FLA. -- Workers in the Payload Hazardous Servicing Facility check fittings for the solar panel (right) they are attaching to Deep Space 1, preparing it for flight in October. The first flight in NASA's New Millennium Program, Deep Space 1 is designed to validate 12 new technologies for scientific space missions of the next century. Onboard experiments include an ion propulsion engine and software that tracks celestial bodies so the spacecraft can make its own navigation decisions without the intervention of ground controllers. Deep Space 1 will complete most of its mission objectives within the first two months, but may also do a flyby of a near-Earth asteroid, 1992 KD, in July 1999. Deep Space 1 will be launched aboard a Boeing Delta 7326 rocket from Launch Pad 17A, Cape Canaveral Air Station. Delta II rockets are medium capacity expendable launch vehicles derived from the Delta family of rockets built and launched since 1960. Since then there have been more than 245 Delta launches

KSC-98pc1181

NASA Image and Video Library

1998-09-29

KENNEDY SPACE CENTER, FLA. -- In the Payload Hazardous Servicing Facility, Tom Shain, project manager on Deep Space 1, displays a CD containing 350,000 names of KSC workers that he will place in a pouch and insert inside the spacecraft. The first flight in NASA's New Millennium Program, Deep Space 1 is designed to validate 12 new technologies for scientific space missions of the next century. Onboard experiments include an ion propulsion engine and software that tracks celestial bodies so the spacecraft can make its own navigation decisions without the intervention of ground controllers. Deep Space 1 will complete most of its mission objectives within the first two months, but may also do a flyby of a near-Earth asteroid, 1992 KD, in July 1999. Deep Space 1 will be launched aboard a Boeing Delta 7326 rocket from Launch Pad 17A, Cape Canaveral Air Station, in October. Delta II rockets are medium capacity expendable launch vehicles derived from the Delta family of rockets built and launched since 1960. Since then there have been more than 245 Delta launches

A new European small platform: Proteus and prospected optical application missions

NASA Astrophysics Data System (ADS)

Dubois, J.-B.; Paoli, F.

2018-04-01

Progress in technology in recent years and new industrial approaches now make it possible to design valuable optical missions using a small-class satellite, like the PROTEUS multi mission platform. Some future space optical missions using existing or planned instruments, combined with the PROTEUS platform, have been assessed by AEROSPATIALE / SPACE and DEFENSE and/or the CNES (French National Space Agency).

Kodak Mirror Assembly Tested at Marshall Space Flight Center

NASA Technical Reports Server (NTRS)

2003-01-01

This photo (rear view) is of one of many segments of the Eastman-Kodak mirror assembly being tested for the James Webb Space Telescope (JWST) project at the X-Ray Calibration Facility at Marshall Space Flight Center (MSFC). MSFC is supporting Goddard Space Flight Center (GSFC) in developing the JWST by taking numerous measurements to predict its future performance. The tests are conducted in a vacuum chamber cooled to approximate the super cold temperatures found in space. During its 27 years of operation, the facility has performed testing in support of a wide array of projects, including the Hubble Space Telescope (HST), Solar A, Chandra technology development, Chandra High Resolution Mirror Assembly and science instruments, Constellation X-Ray Mission, and Solar X-Ray Imager, currently operating on a Geostationary Operational Environment Satellite. The JWST is NASA's next generation space telescope, a successor to the Hubble Space Telescope, named in honor of NASA's second administrator, James E. Webb. It is scheduled for launch in 2010 aboard an expendable launch vehicle. It will take about 3 months for the spacecraft to reach its destination, an orbit of 940,000 miles in space.

Oceanographic Measurements Program Review.

DTIC Science & Technology

1982-03-01

prototype Advanced Microstructure Profiler (AMP) was completed and the unit was operationally tested in local waters (Lake Washington and Puget Sound ...Expendables ....... ............. ..21 A.W. Green The Developent of an Air-Launched ................ 25 Expendable Sound Velocimeter (AXSV); R. Bixby...8217., ,? , .’,*, ;; .,’...; "’ . :" .* " . .. ". ;’ - ~ ~ ~ ~ ’ V’ 7T W, V a .. -- THE DEVELOPMENT OF AN AIR-LAUNCHED EXPENDABLE SOUND VELOCIMETER (AXSV) Richard Bixby

45 CFR 263.1 - How much State money must a State expend annually to meet the basic MOE requirement?

Code of Federal Regulations, 2010 CFR

2010-10-01

... 45 Public Welfare 2 2010-10-01 2010-10-01 false How much State money must a State expend annually... State's Maintenance of Effort? § 263.1 How much State money must a State expend annually to meet the... historic State expenditures. (2) However, if a State meets the minimum work participation rate requirements...

Report of the committee on a commercially developed space facility

NASA Technical Reports Server (NTRS)

Shea, Joseph F.; Stever, H. Guyford; Cutter, W. Bowman, III; Demisch, Wolfgang H.; Fink, Daniel J.; Flax, Alexander H.; Gatos, Harry C.; Glicksman, Martin E.; Lanzerotti, Louis J.; Logsdon, John M., III

1989-01-01

Major facilities that could support significant microgravity research and applications activity are discussed. The ground-based facilities include drop towers, aircraft flying parabolic trajectories, and sounding rockets. Facilities that are intrinsically tied to the Space Shuttle range from Get-Away-Special canisters to Spacelab long modules. There are also orbital facilities which include recoverable capsules launched on expendable launch vehicles, free-flying spacecraft, and space stations. Some of these existing, planned, and proposed facilities are non-U.S. in origin, but potentially available to U.S. investigators. In addition, some are governmentally developed and operated whereas others are planned to be privately developed and/or operated. Tables are provided to show the facility, developer, duration, estimated gravity level, crew interaction, flight frequency, year available, power to payload, payload volume, and maximum payload mass. The potential of direct and indirect benefits of manufacturing in space are presented.

VAB Platform K(2) Lift & Install into Highbay 3

NASA Image and Video Library

2016-03-07

Work is underway to secure the second half of the K-level work platforms for NASA’s Space Launch System (SLS) rocket in High Bay 3 inside the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. The platform is being secured into position on tower E, about 86 feet above the floor. The K work platforms will provide access to NASA's Space Launch System (SLS) core stage and solid rocket boosters during processing and stacking operations on the mobile launcher. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to High Bay 3 to support processing of the SLS and Orion spacecraft. A total of 10 levels of new platforms, 20 platform halves altogether, will surround the SLS rocket and Orion spacecraft.

Space Station tethered waste disposal

NASA Technical Reports Server (NTRS)

Rupp, Charles C.

1988-01-01

The Shuttle Transportation System (STS) launches more payload to the Space Station than can be returned creating an accumulation of waste. Several methods of deorbiting the waste are compared including an OMV, solid rocket motors, and a tether system. The use of tethers is shown to offer the unique potential of having a net savings in STS launch requirement. Tether technology is being developed which can satisfy the deorbit requirements but additional effort is required in waste processing, packaging, and container design. The first step in developing this capability is already underway in the Small Expendable Deployer System program. A developmental flight test of a tether initiated recovery system is seen as the second step in the evolution of this capability.

Performance Qualification Test of the ISS Water Processor Assembly (WPA) Expendables

NASA Technical Reports Server (NTRS)

Carter, Layne; Tabb, David; Tatara, James D.; Mason, Richard K.

2005-01-01

The Water Processor Assembly (WPA) for use on the International Space Station (ISS) includes various technologies for the treatment of waste water. These technologies include filtration, ion exchange, adsorption, catalytic oxidation, and iodination. The WPA hardware implementing portions of these technologies, including the Particulate Filter, Multifiltration Bed, Ion Exchange Bed, and Microbial Check Valve, was recently qualified for chemical performance at the Marshall Space Flight Center. Waste water representing the quality of that produced on the ISS was generated by test subjects and processed by the WPA. Water quality analysis and instrumentation data was acquired throughout the test to monitor hardware performance. This paper documents operation of the test and the assessment of the hardware performance.

Ensuring Payload Safety in Missions with Special Partnerships

NASA Technical Reports Server (NTRS)

Staubus, Calvert A.; Willenbring, Rachel C.; Blankenship, Michael D.

2016-01-01

The National Aeronautics and Space Administration (NASA) Expendable Launch Vehicle (ELV) payload space flight missions involve cooperative work between NASA and partners including spacecraft (or payload) contractors, universities, nonprofit research centers, Agency payload organization, Range Safety organization, Agency launch service organizations, and launch vehicle contractors. The role of NASA's Safety and Mission Assurance (SMA) Directorate is typically fairly straightforward, but when a mission's partnerships become more complex, to realize cost and science benefits (e.g., multi-agency payload(s) or cooperative international missions), the task of ensuring payload safety becomes much more challenging. This paper discusses lessons learned from NASA safety professionals working multiple-agency missions and offers suggestions to help fellow safety professionals working multiple-agency missions.

Earth Science

NASA Image and Video Library

1995-12-02

The Solar Heliospheric Observatory (SOHO) is launched atop an ATLAS-IIAS expendable launch vehicle. Liftoff from launch complex 36B at Cape Canaveral Air Station marked the 10th Atlas launch from the Eastern range for 1995. SOHO is a cooperative effort involving NASA and the European Space Agency (ESA) within the framework of the International Solar-Terrestrial Physics Program. During its 2-year mission, the SOHO spacecraft gathered data on the internal structure of the Sun, its extensive outer atmosphere and the origin of the solar wind.

Space Station logistic support by Aries

NASA Astrophysics Data System (ADS)

Cougnet, C.; Groepper, P.

1987-10-01

The architecture and functions of Aries, a low-cost expendable vehicle, are discussed. The Aries design is based on the Ariane 5 L5 and VEB. The major components of Aries are upgraded L5 and VEB and a payload adaptor; the design and operations of these components are described. The avionics and propulsion system for Aries are examined. Aries is to be employed for logistic support, assembly, and the placement of satellites. An example of a mission scenario and diagrams of Aries are provided.

Reduced Flexibility in Processing Titan IV Space Launch Vehicles at Cape Canaveral Air Force Station.

DTIC Science & Technology

1988-04-01

processing Titan expendable launch vehicles. This study explores the history of those decisions and their effects. It identifies the throughput...HIGH ELL 5PIF ERST BAY TITANI SAM aL’L FIGURE 1.1 SOLID MOTOR ASSEMBLY BUILDING Therefore, DOD decided to convert two of the four Titan solid rocket...required to process a component is based on a 22-year history of assembling and launching Titan vehicles. During this time, the contractor has become

Improving the Cost Estimation of Space Systems. Past Lessons and Future Recommendations

DTIC Science & Technology

2008-01-01

a reasonable gauge for the relative propor- tions of cost growth attributable to errors, decisions, and other causes in any MDAP. Analysis of the...program. The program offices visited were the Defense Metrological Satellite Pro- gram (DMSP), Evolved Expendable Launch Vehicle (EELV), Advanced...3 years 1.8 0.9 3–8 years 1.8 0.9 8+ years 3.7 1.8 Staffing Requirement 7.4 3.7 areas represent earned value and budget drills ; the tan area on top

Building a Metric

NASA Technical Reports Server (NTRS)

Spencer, Shakira

2007-01-01

Launch Services Program is a Kennedy Space Center based program whose job it is to undertake all the necessary roles required to successfully launch Expendable Launch Vehicles. This project was designed to help Launch Services Program accurately report how successful they have been at launching missions on time or +/- 2 days from the scheduled launch date and also if they weren't successful, why. This information will be displayed in the form of a metric, which answers these questions in a clear and accurate way.

Chronology of KSC and KSC related events, 1982

NASA Technical Reports Server (NTRS)

Nail, K., Jr.

1984-01-01

The history of activities at the Kennedy Space Center in 1982 is presented as reflected in NASA News Releases and selected periodicals. Items are arranged in chronological order by date of the published sources. Actual data date of the event may be indicated in parenthesis when the article itself does not make that information explicit. Highlights of the year's activities include three launchings of the orbiter Columbia; successful launches of communications satellites using expendable vehicles; major changes in contracting; and the selection of a base operations contractor.

Characteristics of Thermal Finestructure in the Southern Yellow Sea and the East China Sea from Airborne Expendable Bathythermograph Measurements

DTIC Science & Technology

2008-01-01

Master Oceanographic Observation Data Set 2 ( MOODS ) maintained by the Naval Oceanographic Office (NAVOCEANO), Stennis Space 3 Center, Mississippi...of the CYF. The 17 SYBG also shows a thermal front induced by the Taiwan Warm Current and/or the uplifted 18 Kuroshio northeast of Taiwan merging...c. Generation mechanism 8 Since the cold Kuroshio subsurface water is uplifted at Stn-A, temperature of Stn-9 A is colder than that of Stn-C at

LSST system analysis and integration task for an advanced science and application space platform

NASA Technical Reports Server (NTRS)

1980-01-01

To support the development of an advanced science and application space platform (ASASP) requirements of a representative set of payloads requiring large separation distances selected from the Science and Applications Space Platform data base. These payloads were a 100 meter diameter atmospheric gravity wave antenna, a 100 meter by 100 meter particle beam injection experiment, a 2 meter diameter, 18 meter long astrometric telescope, and a 15 meter diameter, 35 meter long large ambient deployable IR telescope. A low earth orbit at 500 km altitude and 56 deg inclination was selected as being the best compromise for meeting payload requirements. Platform subsystems were defined which would support the payload requirements and a physical platform concept was developed. Structural system requirements which included utilities accommodation, interface requirements, and platform strength and stiffness requirements were developed. An attitude control system concept was also described. The resultant ASASP concept was analyzed and technological developments deemed necessary in the area of large space systems were recommended.

Evolution of a Reconfigurable Processing Platform for a Next Generation Space Software Defined Radio

NASA Technical Reports Server (NTRS)

Kacpura, Thomas J.; Downey, Joseph A.; Anderson, Keffery R.; Baldwin, Keith

2014-01-01

The National Aeronautics and Space Administration (NASA)Harris Ka-Band Software Defined Radio (SDR) is the first, fully reprogrammable space-qualified SDR operating in the Ka-Band frequency range. Providing exceptionally higher data communication rates than previously possible, this SDR offers in-orbit reconfiguration, multi-waveform operation, and fast deployment due to its highly modular hardware and software architecture. Currently in operation on the International Space Station (ISS), this new paradigm of reconfigurable technology is enabling experimenters to investigate navigation and networking in the space environment.The modular SDR and the NASA developed Space Telecommunications Radio System (STRS) architecture standard are the basis for Harris reusable, digital signal processing space platform trademarked as AppSTAR. As a result, two new space radio products are a synthetic aperture radar payload and an Automatic Detection Surveillance Broadcast (ADS-B) receiver. In addition, Harris is currently developing many new products similar to the Ka-Band software defined radio for other applications. For NASAs next generation flight Ka-Band radio development, leveraging these advancements could lead to a more robust and more capable software defined radio.The space environment has special considerations different from terrestrial applications that must be considered for any system operated in space. Each space mission has unique requirements that can make these systems unique. These unique requirements can make products that are expensive and limited in reuse. Space systems put a premium on size, weight and power. A key trade is the amount of reconfigurability in a space system. The more reconfigurable the hardware platform, the easier it is to adapt to the platform to the next mission, and this reduces the amount of non-recurring engineering costs. However, the more reconfigurable platforms often use more spacecraft resources. Software has similar considerations to hardware. Having an architecture standard promotes reuse of software and firmware. Space platforms have limited processor capability, which makes the trade on the amount of amount of flexibility paramount.

Second interim briefing (D3). Evolutionary Science and Applications Space Platform. Characterization of concepts, tasks A and B

NASA Technical Reports Server (NTRS)

1981-01-01

The objectives were to define, evaluate, and select concepts for evolving a space station in conjunction with the Space Platform for NASA science, Applications, Technology and DOD; and a permanently manned presence in space early, with a maximum of existing technology.

KSC-97PC1064

NASA Image and Video Library

1997-07-18

Jet Propulsion Laboratory (JPL) workers carefully roll into place a platform with a second radioisotope thermoelectric generator (RTG) for installation on the Cassini spacecraft. In background at left, the first of three RTGs already has been installed on Cassini. The RTGs will provide electrical power to Cassini on its 6.7-year trip to the Saturnian system and during its four-year mission at Saturn. The power units are undergoing mechanical and electrical verification testing in the Payload Hazardous Servicing Facility. RTGs use heat from the natural decay of plutonium to generate electric power. The generators enable spacecraft to operate far from the Sun where solar power systems are not feasible. The Cassini mission is scheduled for an Oct. 6 launch aboard a Titan IVB/Centaur expendable launch vehicle. Cassini is built and managed for NASA by JPL

Around Marshall

NASA Image and Video Library

2003-04-09

This photo (a frontal view) is of one of many segments of the Eastman-Kodak mirror assembly being tested for the James Webb Space Telescope (JWST) project at the X-Ray Calibration Facility at Marshall Space Flight Center (MSFC). MSFC is supporting Goddard Space Flight Center (GSFC) in developing the JWST by taking numerous measurements to predict its future performance. The tests are conducted in a vacuum chamber cooled to approximate the super cold temperatures found in space. During its 27 years of operation, the facility has performed testing in support of a wide array of projects, including the Hubble Space Telescope (HST), Solar A, Chandra technology development, Chandra High Resolution Mirror Assembly and science instruments, Constellation X-Ray Mission, and Solar X-Ray Imager, currently operating on a Geostationary Operational Environment Satellite. The JWST is NASA's next generation space telescope, a successor to the Hubble Space Telescope, named in honor of NASA's second administrator, James E. Webb. It is scheduled for launch in 2010 aboard an expendable launch vehicle. It will take about 3 months for the spacecraft to reach its destination, an orbit of 940,000 miles in space.

KSC-98pc1177

NASA Image and Video Library

1998-09-29

KENNEDY SPACE CENTER, FLA. -- In the Payload Hazardous Servicing Facility, the media (below), dressed in "bunny" suits, learn about Deep Space 1 from Leslie Livesay (facing cameras), Deep Space 1 spacecraft manager from the Jet Propulsion Laboratory. In the background, KSC workers place insulating blankets on Deep Space 1. The first flight in NASA's New Millennium Program, Deep Space 1 is designed to validate 12 new technologies for scientific space missions of the next century. Onboard experiments include an ion propulsion engine and software that tracks celestial bodies so the spacecraft can make its own navigation decisions without the intervention of ground controllers. Deep Space 1 will complete most of its mission objectives within the first two months, but may also do a flyby of a near-Earth asteroid, 1992 KD, in July 1999. Deep Space 1 will be launched aboard a Boeing Delta 7326 rocket from Launch Pad 17A, Cape Canaveral Air Station, in October. Delta II rockets are medium capacity expendable launch vehicles derived from the Delta family of rockets built and launched since 1960. Since then there have been more than 245 Delta launches

Report of the Committee on the Space Station of the National Research Council

NASA Technical Reports Server (NTRS)

1987-01-01

The Space Station Program will be the most ambitious space project the nation has ever undertaken; will require tens of billions of dollars; and will entwine for many years the space program with those of international partners. It must have enduring stable support across administrations, and the support must be generous. The current Space Shuttle is barely adequate for the limited purpose of deploying the Space Station, and it is inadequate to meet broader national needs in space. The Committee recommends in the strongest terms that the Shuttle be upgraded with new improved solid rocket motors, that it be supplemented with expendable launch vehicles, and that a heavy lift launch vehicle be developed for use in the latter half of the 1990s. The Committee strongly recommends that NASA prepare a new Space Station Program cost estimate in conjunction with the Program Requirements Review scheduled for early next year by NASA. The exercise should address the full range of uncertainties in the current Program, some of which are discussed in the report.

Platform options for the Space Station program

NASA Technical Reports Server (NTRS)

Mangano, M. J.; Rowley, R. W.

1986-01-01

Platforms for polar and 28.5 deg orbits were studied to determine the platform requirements and characteristics necessary to support the science objectives. Large platforms supporting the Earth-Observing System (EOS) were initially studied. Co-orbiting platforms were derived from these designs. Because cost estimates indicated that the large platform approach was likely to be too expensive, require several launches, and generally be excessively complex, studies of small platforms were undertaken. Results of these studies show the small platform approach to be technically feasible at lower overall cost. All designs maximized hardware inheritance from the Space Station program to reduce costs. Science objectives as defined at the time of these studies are largely achievable.

The Importance of Conducting Life Sciences Experiments on the Deep Space Gateway Platform

NASA Astrophysics Data System (ADS)

Bhattacharya, S.

2018-02-01

Life science research on the Deep Space Gateway platform is an important precursor for long term human exploration of deep space. Ideas for utilizing flight hardware and well characterized model organisms will be discussed.

A Framework for Assessing the Reusability of Hardware (Reusable Rocket Engines)

NASA Technical Reports Server (NTRS)

Childress-Thompson, Rhonda; Farrington, Philip; Thomas, Dale

2016-01-01

Within the space flight community, reusability has taken center stage as the new buzzword. In order for reusable hardware to be competitive with its expendable counterpart, two major elements must be closely scrutinized. First, recovery and refurbishment costs must be lower than the development and acquisition costs. Additionally, the reliability for reused hardware must remain the same (or nearly the same) as "first use" hardware. Therefore, it is imperative that a systematic approach be established to enhance the development of reusable systems. However, before the decision can be made on whether it is more beneficial to reuse hardware or to replace it, the parameters that are needed to deem hardware worthy of reuse must be identified. For reusable hardware to be successful, the factors that must be considered are reliability (integrity, life, number of uses), operability (maintenance, accessibility), and cost (procurement, retrieval, refurbishment). These three factors are essential to the successful implementation of reusability while enabling the ability to meet performance goals. Past and present strategies and attempts at reuse within the space industry will be examined to identify important attributes of reusability that can be used to evaluate hardware when contemplating reusable versus expendable options. This paper will examine why reuse must be stated as an initial requirement rather than included as an afterthought in the final design. Late in the process, changes in the overall objective/purpose of components typically have adverse effects that potentially negate the benefits. A methodology for assessing the viability of reusing hardware will be presented by using the Space Shuttle Main Engine (SSME) to validate the approach. Because reliability, operability, and costs are key drivers in making this critical decision, they will be used to assess requirements for reuse as applied to components of the SSME.

Space Suit Radiator Performance in Lunar and Mars Environments

NASA Technical Reports Server (NTRS)

Paul, Heather; Trevino, Luis; Nabity, James; Mason, Georgia; Copeland, Robert; Libberton, Kerry; Stephan, Ryan

2007-01-01

During an ExtraVehicular Activity (EVA), both the heat generated by the astronaut's metabolism and that produced by the Portable Life Support System (PLSS) must be rejected to space. The heat sources include the heat of adsorption of metabolic CO2, the heat of condensation of water, the heat removed from the body by the liquid cooling garment and the load from the electrical components. Although the sublimator hardware to reject this load weighs only 3.48 lbs, an additional eight pounds of water are loaded into the unit of which about six to eight are sublimated and lost; this is the single largest expendable during an eight-hour EVA. Using a radiator to reject heat from the Astronaut during an EVA, we can significantly reduce the amount of expendable water consumed by the sublimator. Last year we reported on the design and initial operational assessment tests of our novel radiator designated the Radiator And Freeze Tolerant heat eXchanger (RAFT-X). Herein, we report on tests conducted in the NASA Johnson Space Center Chamber E Thermal Vacuum Test Facility. Up to 800 Btu/h of heat were rejected in lunar and Mars environments with temperatures as cold as 150 F. Tilting the radiator did not cause an observable loss in performance. The RAFT-X endured freeze/thaw cycles and in fact, the heat exchanger was completely frozen three times without any apparent damage to the unit. We were also able to operate the heat exchanger in a partially frozen configuration to throttle the heat rejection rate from 530 Btu/h at low water flow rate down to 300 Btu/h. Finally, the deliberate loss of a single loop heat pipe only degraded the heat rejection performance by about 2 to 5%.

Space Suit Radiator Performance in Lunar and Mars Environments

NASA Technical Reports Server (NTRS)

Nabity, James; Mason, Georgia; Copeland, Robert; Libberton, Kerry; Trevino, Luis; Stephan, Ryan; Paul, Heather

2007-01-01

During an ExtraVehicular Activity (EVA), both the heat generated by the astronaut's metabolism and that produced by the Portable Life Support System (PLSS) must be rejected to space. The heat sources include the heat of adsorption of metabolic CO2, the heat of condensation of water, the heat removed from the body by the liquid cooling garment and the load from the electrical components. Although the sublimator hardware to reject this load weighs only 3.48 lbs, an additional eight pounds of water are loaded into the unit of which about six to eight are sublimated and lost; this is the single largest expendable during an eight-hour EVA. Using a radiator to reject heat from the Astronaut during an EVA, we can significantly reduce the amount of expendable water consumed by the sublimator. Last year we reported on the design and initial operational assessment tests of our novel radiator designated the Radiator And Freeze Tolerant heat eXchanger (RAFT-X). Herein, we report on tests conducted in the NASA Johnson Space Center Chamber E Thermal Vacuum Test Facility. Up to 800 Btu/h of heat were rejected in lunar and Mars environments with temperatures as cold as -150 F. Tilting the radiator did not cause an observable loss in performance. The RAFT-X endured freeze / thaw cycles and in fact, the heat exchanger was completely frozen three times without any apparent damage to the unit. We were also able to operate the heat exchanger in a partially frozen configuration to throttle the heat rejection rate from 530 Btu/h at low water flow rate down to 300 Btu/h. Finally, the deliberate loss of a single loop heat pipe only degraded the heat rejection performance by about 2 to 5%.

Next generation sensing platforms for extended deployments in large-scale, multidisciplinary, adaptive sampling and observational networks

NASA Astrophysics Data System (ADS)

Cross, J. N.; Meinig, C.; Mordy, C. W.; Lawrence-Slavas, N.; Cokelet, E. D.; Jenkins, R.; Tabisola, H. M.; Stabeno, P. J.

2016-12-01

New autonomous sensors have dramatically increased the resolution and accuracy of oceanographic data collection, enabling rapid sampling over extremely fine scales. Innovative new autonomous platofrms like floats, gliders, drones, and crawling moorings leverage the full potential of these new sensors by extending spatiotemporal reach across varied environments. During 2015 and 2016, The Innovative Technology for Arctic Exploration Program at the Pacific Marine Environmental Laboratory tested several new types of fully autonomous platforms with increased speed, durability, and power and payload capacity designed to deliver cutting-edge ecosystem assessment sensors to remote or inaccessible environments. The Expendable Ice-Tracking (EXIT) gloat developed by the NOAA Pacific Marine Environmental Laboratory (PMEL) is moored near bottom during the ice-free season and released on an autonomous timer beneath the ice during the following winter. The float collects a rapid profile during ascent, and continues to collect critical, poorly-accessible under-ice data until melt, when data is transmitted via satellite. The autonomous Oculus sub-surface glider developed by the University of Washington and PMEL has a large power and payload capacity and an enhanced buoyancy engine. This 'coastal truck' is designed for the rapid water column ascent required by optical imaging systems. The Saildrone is a solar and wind powered ocean unmanned surface vessel (USV) developed by Saildrone, Inc. in partnership with PMEL. This large-payload (200 lbs), fast (1-7 kts), durable (46 kts winds) platform was equipped with 15 sensors designed for ecosystem assessment during 2016, including passive and active acoustic systems specially redesigned for autonomous vehicle deployments. The senors deployed on these platforms achieved rigorous accuracy and precision standards. These innovative platforms provide new sampling capabilities and cost efficiencies in high-resolution sensor deployment, including reconnaissance for annual fisheries and marine mammal surveys; better linkages between sustained observing platforms; and adaptive deployments that can easily target anomalies as they arise.

A Novel Sensor Platform Matching the Improved Version of IPMVP Option C for Measuring Energy Savings

PubMed Central

Tseng, Yen-Chieh; Lee, Da-Sheng; Lin, Cheng-Fang; Chang, Ching-Yuan

2013-01-01

It is easy to measure energy consumption with a power meter. However, energy savings cannot be directly computed by the powers measured using existing power meter technologies, since the power consumption only reflects parts of the real energy flows. The International Performance Measurement and Verification Protocol (IPMVP) was proposed by the Efficiency Valuation Organization (EVO) to quantify energy savings using four different methodologies of A, B, C and D. Although energy savings can be estimated following the IPMVP, there are limitations on its practical implementation. Moreover, the data processing methods of the four IPMVP alternatives use multiple sensors (thermometer, hygrometer, Occupant information) and power meter readings to simulate all facilities, in order to determine an energy usage benchmark and the energy savings. This study proposes a simple sensor platform to measure energy savings. Using usually the Electronic Product Code (EPC) global standard, an architecture framework for an information system is constructed that integrates sensors data, power meter readings and occupancy conditions. The proposed sensor platform is used to monitor a building with a newly built vertical garden system (VGS). A VGS shields solar radiation and saves on energy that would be expended on air-conditioning. With this platform, the amount of energy saved in the whole facility is measured and reported in real-time. The data are compared with those obtained from detailed measurement and verification (M&V) processes. The discrepancy is less than 1.565%. Using measurements from the proposed sensor platform, the energy savings for the entire facility are quantified, with a resolution of ±1.2%. The VGS gives an 8.483% daily electricity saving for the building. Thus, the results show that the simple sensor platform proposed by this study is more widely applicable than the four complicated IPMVP alternatives and the VGS is an effective tool in reducing the carbon footprint of a building. PMID:23698273

Front view of the Orbiter Discovery from an elevated platform ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Front view of the Orbiter Discovery from an elevated platform in the Vehicle Assembly Building at NASA's Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

jsc2018m000314_Spinning_Science_Multi-use_Variable-g_Platform_Arrives_at_the_Space_Station-MP4

NASA Image and Video Library

2018-05-09

Spinning Science: Multi-use Variable-g Platform Arrives at the Space Station --- The Multi-use Variable-gravity Platform (MVP) Validation mission will install and test the MVP, a new hardware platform developed and owned by Techshot Inc., on the International Space Station (ISS). Though the MVP is designed for research with many different kinds of organisms and cell types, this validation mission will focus on Drosophila melanogaster, more commonly known as the fruit fly. This platform will be especially important for fruit fly research, as it will allow researchers to study larger sample sizes of Drosophila melanogaster than in other previous hardware utilizing centrifuges and it will be able to support fly colonies for multiple generations.

A Systems Approach to Lower Cost Missions: Following the Rideshare Paradigm

NASA Technical Reports Server (NTRS)

Herrell, L.

2009-01-01

Small-satellite rideshare capabilities and opportunities for low-cost access to space have been evolving over the past 10 years. Small space launch vehicle technology is rapidly being developed and demonstrated, including the Minotaur series and the Space X Falcon, among others, along with the lower cost launch facilities at Alaska's Kodiak Launch Complex, NASA's Wallops Flight Facility, and the Reagan Test Site in the Pacific. Demonstrated capabilities for the launch of multiple payloads have increased (and continue to increase) significantly. This will allow more efficient and cost-effective use of the various launch opportunities, including utilizing the excess capacity of the emerging Evolved Expendable Launch Vehicle (EELV)-based missions. The definition of standardized interfaces and processes, along with various user guides and payload implementation plans, has been developed and continues to be refined. Top-level agency policies for the support of low-cost access to space for small experimental payloads, such as the DoD policy structure on auxiliary payloads, have been defined and provide the basis for the continued refinement and implementation of these evolving technologies. Most importantly, the coordination and cooperative interfaces between the various stakeholders continues to evolve. The degree of this coordination and technical interchange is demonstrated by the wide stakeholder participation at the recent 2008 Small Payload Rideshare Workshop, held at NASA's Wallops Flight Facility. This annual workshop has been the major platform for coordination and technical interchange within the rideshare community and with the various sponsoring agencies. These developments have provided the foundation for a robust low-cost small payload rideshare capability. However, the continued evolution, sustainment, and utilization of these capabilities will require continued stakeholder recognition, support, and nourishing. Ongoing, coordinated effort, partnering, and support between stakeholders is essential to acquire the improved organizational processes and efficiencies required to meet the needs of the growing small payload community for low-cost access to space. Further, a mix of capabilities developed within the space community for Operationally Responsive Space, an international committee investigating space systems cross-compatibility, and an industry-based organization seeking small satellite "standardization" all work toward a new paradigm: sharing or leveraging resources amongst multiple users. The challenge: where are those users, and what is the best way to leverage them? What is leveraged-mass, power, cost-sharing? And how does one sort through these options? What policies may prevent the use of some options? Who are the "other users" that might share or leverage capabilities? This paper presents a systematic look at both the users and the launch options, and suggests a way forward.

Liquid Space Lubricants Examined by Vibrational Micro-Spectroscopy

NASA Technical Reports Server (NTRS)

Street, Kenneth W., Jr.

2008-01-01

Considerable effort has been expended to develop liquid lubricants for satellites and space exploration vehicles. These lubricants must often perform under a range of harsh conditions such as vacuum, radiation, and temperature extremes while in orbit or in transit and in extremely dusty environments at destinations such as the Moon and Mars. Historically, oil development was guided by terrestrial application, which did not provide adequate space lubricants. Novel fluids such as the perfluorinated polyethers provided some relief but are far from ideal. With each new fluid proposed to solve one problem, other problems have arisen. Much of the work performed at the National Aeronautics and Space Administration (NASA) Glenn Research Center (GRC) in elucidating the mechanisms by which chemical degradation of space oils occur has been done by vibrational micro-spectroscopic techniques such as infrared and Raman, which this review details. Presented are fundamental lubrication studies as well as actual case studies in which vibrational spectroscopy has led to millions of dollars in savings and potentially prevented loss of mission.

United Space Alliance waits to test its one-man submarine for SRB retrieval

NASA Technical Reports Server (NTRS)

2000-01-01

The one-man submarine dubbed DeepWorker 2000 sits on the deck of Liberty Star, one of two KSC solid rocket booster recovery ships. Inside the sub is the pilot, Anker Rasmussen. The sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program.

Habitat and logistic support requirements for the initiation of a space manufacturing enterprise

NASA Technical Reports Server (NTRS)

Vajk, J. P.; Engel, J. H.; Shettler, J. A.

1979-01-01

A detailed scenario for the initiation of a space manufacturing enterprise using lunar materials to construct solar power satellites (SPS) was developed, with particular attention to habitat design and logistic support requirements. If SPS's can be constructed exclusively from lunar materials, the entire enterprise can be initiated in a 7 year period of launch activity (beginning as early as 1985) using the Space Shuttle and a low-cost, Shuttle-derived heavy lift vehicle. If additional chemical feedstocks must be imported from earth in significant quantities, it may be necessary to bring the next-generation launch vehicle (single-stage-to-orbit) into operation by 1991. The scenario presented features use of the mass-driver reaction engine for orbit-to-orbit transfer of cargos and makes extensive use of the expendable Shuttle external propellant tanks.

Materials and processes for shuttle engine, external tank, and solid rocket booster

NASA Technical Reports Server (NTRS)

Schwinghamer, R. J.

1977-01-01

The Shuttle flight system is composed of the Orbiter, an External Tank (ET) that contains the ascent propellant to be used by the Space Shuttle Main Engines (SSME), and two Solid Rocket Boosters (SRB). The ET is expended on each launch; the Orbiter and SRB's are reusable. It is the requirement for reuse which poses the exciting new materials and processes challenges in the development of the Space Shuttle. A brief description of the Space Shuttle and the mission profile is given. The Shuttle configuration is then described with emphasis on the SSME, ET, and SRB. The materials selection, tracking, and control system used to assure reliability and to minimize cost are described, and salient features and challenges in materials and processes associated with the SSME, ET, and SRB are subsequently discussed.

Interrelationship between Plasma Experiments in the Laboratory and in Space

DOE Office of Scientific and Technical Information (OSTI.GOV)

Koepke, Mark E.

Funds were expended to offset the travel costs of three students and three postdoctoral research associates to participate in and present work at the 2015 International Workshop on the Interrelationship between Plasma Experiments in the Laboratory and in Space (IPELS2015), 23-28 August 2015, Pitlochry, Scotland, UK. Selection was priority-ranked by lab-space engagement, first, and topic relevance, second. Supplementary selection preference was applied to under-represented populations, applicants lacking available travel-resources in their home research group, applicants unusually distant from the conference venue, and the impact of the applicant’s attendance in increasing the diversity of conference participation. One support letter per studentmore » was required. The letters described the specific benefit of IPELS2015 to the student dissertation or the postdoc career development, and document the evidence for the ordering criteria.« less

Floor Plans Rolling Platform, Tech Systems Platform, and Load ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Floor Plans - Rolling Platform, Tech Systems Platform, and Load Platform Plans - Marshall Space Flight Center, F-1 Engine Static Test Stand, On Route 565 between Huntsville and Decatur, Huntsville, Madison County, AL

Reagentless chemiluminescence-based fiber optic sensors for regenerative life support in space

NASA Astrophysics Data System (ADS)

Atwater, James E.; Akse, James R.; DeHart, Jeffrey; Wheeler, Richard R., Jr.

1995-04-01

The initial feasibility demonstration of a reagentless chemiluminescence based fiber optic sensor technology for use in advanced regenerative life support applications in space and planetary outposts is described. The primary constraints for extraterrestrial deployment of any technology are compatibility with microgravity and hypogravity environments; minimal size, weight, and power consumption; and minimal use of expendables due to the great expense and difficulty inherent to resupply logistics. In the current research, we report the integration of solid state flow through modules for the production of aqueous phase reagents into an integrated system for the detection of important analytes by chemiluminescence, with fiber optic light transmission. By minimizing the need for resupply expendables, the use of solid phase modules makes complex chemical detection schemes practical. For the proof of concept, hydrogen peroxide and glucose were chosen as analytes. The reaction is catalyzed by glucose oxidase, an immobilized enzyme. The aqueous phase chemistry required for sensor operation is implemented using solid phase modules which adjust the pH of the influent stream, catalyze the oxidation of analyte, and provide the controlled addition of the luminophore to the flowing aqueous stream. Precise control of the pH has proven essential for the long-term sustained release of the luminophore. Electrocatalysis is achieved using a controlled potential across gold mesh and gold foil electrodes which undergo periodic polarity reversals. The development and initial characterization of performance of the reagentless fiber optic chemiluminescence sensors are presented in this paper.

The European Space Agency's FESTIP initiative

NASA Astrophysics Data System (ADS)

Burleson, Daphne

1998-01-01

In an effort to reduce the cost of access and open up new markets, the European Space Agency has begun a program called Future European Space Transportation Investigations Programme or FESTIP, in which reusable launcher concepts are being studied and developed. The ideal reusable launcher would be comparable to a normal aircraft in that it would be capable of taking off from many possible locations on Earth, enter the desired orbital plane, then accelerate to orbital velocity, release its payload, de-orbit, disperse its kinetic energy and land at the take-off base to be prepared for its next flight following a quick turnaround time. This ideal vehicle would be called the `single-stage-to-orbit reusable rocket launcher' or SSTO-RRL. All space launchers currently in use are staged to orbit and expendable, except the US Space Shuttle, and there is no SSTO-RRL in operation as yet. This paper will discuss the design options being studied by the European Space Agency (ESA) as well as their practical use in serving the space-launch market (FESTIP Workshop 1).

CRYOTE (Cryogenic Orbital Testbed) Concept

NASA Technical Reports Server (NTRS)

Gravlee, Mari; Kutter, Bernard; Wollen, Mark; Rhys, Noah; Walls, Laurie

2009-01-01

Demonstrating cryo-fluid management (CFM) technologies in space is critical for advances in long duration space missions. Current space-based cryogenic propulsion is viable for hours, not the weeks to years needed by space exploration and space science. CRYogenic Orbital TEstbed (CRYOTE) provides an affordable low-risk environment to demonstrate a broad array of critical CFM technologies that cannot be tested in Earth's gravity. These technologies include system chilldown, transfer, handling, health management, mixing, pressure control, active cooling, and long-term storage. United Launch Alliance is partnering with Innovative Engineering Solutions, the National Aeronautics and Space Administration, and others to develop CRYOTE to fly as an auxiliary payload between the primary payload and the Centaur upper stage on an Atlas V rocket. Because satellites are expensive, the space industry is largely risk averse to incorporating unproven systems or conducting experiments using flight hardware that is supporting a primary mission. To minimize launch risk, the CRYOTE system will only activate after the primary payload is separated from the rocket. Flying the testbed as an auxiliary payload utilizes Evolved Expendable Launch Vehicle performance excess to cost-effectively demonstrate enhanced CFM.

DEEP SPACE: High Resolution VR Platform for Multi-user Interactive Narratives

NASA Astrophysics Data System (ADS)

Kuka, Daniela; Elias, Oliver; Martins, Ronald; Lindinger, Christopher; Pramböck, Andreas; Jalsovec, Andreas; Maresch, Pascal; Hörtner, Horst; Brandl, Peter

DEEP SPACE is a large-scale platform for interactive, stereoscopic and high resolution content. The spatial and the system design of DEEP SPACE are facing constraints of CAVETM-like systems in respect to multi-user interactive storytelling. To be used as research platform and as public exhibition space for many people, DEEP SPACE is capable to process interactive, stereoscopic applications on two projection walls with a size of 16 by 9 meters and a resolution of four times 1080p (4K) each. The processed applications are ranging from Virtual Reality (VR)-environments to 3D-movies to computationally intensive 2D-productions. In this paper, we are describing DEEP SPACE as an experimental VR platform for multi-user interactive storytelling. We are focusing on the system design relevant for the platform, including the integration of the Apple iPod Touch technology as VR control, and a special case study that is demonstrating the research efforts in the field of multi-user interactive storytelling. The described case study, entitled "Papyrate's Island", provides a prototypical scenario of how physical drawings may impact on digital narratives. In this special case, DEEP SPACE helps us to explore the hypothesis that drawing, a primordial human creative skill, gives us access to entirely new creative possibilities in the domain of interactive storytelling.

Platform C Installation

NASA Image and Video Library

2016-10-19

A heavy-lift crane lowers the first half of the C-level work platforms, C south, for NASA’s Space Launch System (SLS) rocket, for installation on the south side of High Bay 3 in the Vehicle Assembly Building (VAB) at NASA’s Kennedy Space Center in Florida. The C platforms are the eighth of 10 levels of work platforms that will surround and provide access to the SLS rocket and Orion spacecraft for Exploration Mission 1. In view below Platform C are several of the previously installed platforms. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to VAB High Bay 3, including installation of the new work platforms, to prepare for NASA’s Journey to Mars.

Applicability and Performance Benefits of XD (Tradename) Titanium Aluminides to Expendable Gas Turbine Engines

DTIC Science & Technology

1993-08-01

analysis A dynamic analysis was conducted on the blades and splitters. The existing design for the compressor was used and XD® titanium aluminide property...AD-A272 998 ARMY RESEARCH LABORATORY Applicability and Performance Benefits of XD® Titanium Aluminides to Expendable Gas Turbine Engines Pamela...Benefits of XD® Contract # Titanium Aluminides to Expendable Gas Turbine DAAL04-91-C-0034 Fnginpq 6. AUTHOR(S) Pamela Sadler, K. Sharvan Kumar, John A. S

Space construction system analysis. Part 2: Platform definition

NASA Technical Reports Server (NTRS)

Hart, R. J.; Myers, H. L.; Abramson, R. D.; Dejong, P. N.; Donavan, R. D.; Greenberg, H. S.; Indrikis, J.; Jandrasi, J. S.; Manoff, M.; Mcbaine, C. K.

1980-01-01

The top level system requirements are summarized and the accompanying conceptual design for an engineering and technology verification platform (ETVP) system is presented. An encompassing statement of the system objectives which drive the system requirements is presented and the major mission and subsystem requirements are described with emphasis on the advanced communications technology mission payload. The platform design is defined and used as a reference configuration for an end to space construction analyses. The preferred construction methods and processes, the important interactions between the platform design and the construction system design and operation, and the technology development efforts required to support the design and space construction of the ETVP are outlined.

Toward a Genome-Wide Systems Biology Analysis of Host-Pathogen Interactions in Group A Streptococcus

PubMed Central

Musser, James M.; DeLeo, Frank R.

2005-01-01

Genome-wide analysis of microbial pathogens and molecular pathogenesis processes has become an area of considerable activity in the last 5 years. These studies have been made possible by several advances, including completion of the human genome sequence, publication of genome sequences for many human pathogens, development of microarray technology and high-throughput proteomics, and maturation of bioinformatics. Despite these advances, relatively little effort has been expended in the bacterial pathogenesis arena to develop and use integrated research platforms in a systems biology approach to enhance our understanding of disease processes. This review discusses progress made in exploiting an integrated genome-wide research platform to gain new knowledge about how the human bacterial pathogen group A Streptococcus causes disease. Results of these studies have provided many new avenues for basic pathogenesis research and translational research focused on development of an efficacious human vaccine and novel therapeutics. One goal in summarizing this line of study is to bring exciting new findings to the attention of the investigative pathology community. In addition, we hope the review will stimulate investigators to consider using analogous approaches for analysis of the molecular pathogenesis of other microbes. PMID:16314461

Floor Plans Engine Removal Platform, Hold Down Arm Platform, ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Floor Plans - Engine Removal Platform, Hold Down Arm Platform, Hydraulic Equipment Platforms, Isometric Cutaway of Engine Removal Platform, Isometric Cutaway of Hold Down Arm Platform, Isometric Cutaway of Hydraulic Platforms and Engine Support System Access - Marshall Space Flight Center, Saturn V S-IC Static Test Facility, West Test Area, Huntsville, Madison County, AL

Platform C Installation

NASA Image and Video Library

2016-10-19

Inside the Vehicle Assembly Building at NASA’s Kennedy Space Center in Florida, construction workers assist with the installation of the first half of the C-level work platforms, C south, for NASA’s Space Launch System (SLS) rocket. The large bolts that hold the platform in place on the south wall are being secured. The C platforms are the eighth of 10 levels of work platforms that will surround and provide access to the SLS rocket and Orion spacecraft for Exploration Mission 1. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to VAB High Bay 3, including installation of the new work platforms, to prepare for NASA’s Journey to Mars.

Platform C Installation

NASA Image and Video Library

2016-10-19

Inside the Vehicle Assembly Building at NASA’s Kennedy Space Center in Florida, the first half of the C-level work platforms, C south, for NASA’s Space Launch System (SLS) rocket, has been installed on the south side of the high bay. In view below are several levels of previously installed platforms. The C platforms are the eighth of 10 levels of work platforms that will surround and provide access to the SLS rocket and Orion spacecraft for Exploration Mission 1. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to VAB High Bay 3, including installation of the new work platforms, to prepare for NASA’s Journey to Mars.

View from second floor platform looking up at subsequent platforms. ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

View from second floor platform looking up at subsequent platforms. Note the Shuttle assembly outlined by the platform edges. - Marshall Space Flight Center, Saturn V Dynamic Test Facility, East Test Area, Huntsville, Madison County, AL

Strawman payload data for science and applications space platforms

NASA Technical Reports Server (NTRS)

1980-01-01

The need for a free flying science and applications space platform to host compatible long duration experiment groupings in Earth orbit is discussed. Experiment level information on strawman payload models is presented which serves to identify and quantify the requirements for the space platform system. A description data base on the strawman payload model is presented along with experiment level and group level summaries. Payloads identified in the strawman model include the disciplines of resources observations and environmental observations.

Space Station as a Long Duration Exposure Facility

NASA Technical Reports Server (NTRS)

Folley, Adrienne; Scheib, Jim

1995-01-01

There is need for a space platform for experiments investigating long duration exposure to space. This platform should be maintainable in the event of a malfunction, and experiments should be easily recoverable for analysis on Earth. The International Space Station provides such a platform. The current Space Station configuration has six external experiment attachment sites, providing utilities and data support distributed along the external truss. There are also other sites that could potentially support long duration exposure experiments. This paper describes the resources provided to payloads at these sites, and cites examples of integration of proposed long duration exposure experiments on these sites. The environments to which external attached payloads will be exposed are summarized.

Lessons learned from and the future for NASA's Small Explorer Program

NASA Technical Reports Server (NTRS)

Newton, George P.

1991-01-01

NASA started the Small Explorer Program to provide space scientists with an opportunity to conduct space science research in the Explorer Program using scientific payloads launched on small-class expendable launch vehicles. A series of small payload, scientific missions was envisioned that could be launched at the rate of one to two missions per year. Three missions were selected in April 1989: Solar Anomalous and Magnetospheric Particle Explorer, Fast Auroral Snapshot Explorer, and Sub-millimeter Wave Astronomy. These missions are planned for launch in June 1992, September 1994 and June 1995, respectively. At a program level, this paper presents the history, objectives, status, and lessons learned which may be applicable to similar programs, and discusses future program plans.

KSC00pp0596

NASA Image and Video Library

2000-04-27

The one-man submarine dubbed DeepWorker 2000 sits on the deck of Liberty Star, one of two KSC solid rocket booster recovery ships. The sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program

KSC-00pp0596

NASA Image and Video Library

2000-04-27

The one-man submarine dubbed DeepWorker 2000 sits on the deck of Liberty Star, one of two KSC solid rocket booster recovery ships. The sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program

KSC00pp0597

NASA Image and Video Library

2000-04-27

The one-man submarine dubbed DeepWorker 2000 sits on the deck of Liberty Star, one of two KSC solid rocket booster recovery ships. The sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program

KSC-00pp0597

NASA Image and Video Library

2000-04-27

The one-man submarine dubbed DeepWorker 2000 sits on the deck of Liberty Star, one of two KSC solid rocket booster recovery ships. The sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program

Study of solid rocket motor for space shuttle booster, volume 2, book 5, appendices E thru H

NASA Technical Reports Server (NTRS)

1972-01-01

Preliminary parametric studies were performed to establish size, weight and packaging arrangements for aerodynamic decelerator devices that could be used for recovery of the expended solid propellant rocket motors used in the launch phase of the Space Shuttle System. Computations were made using standard engineering analysis techniques. Terminal stage parachutes were sized to provide equilibrium descent velocities for water entry that are presently thought to be acceptable without developing loads that could exceed the boosters structural integrity. The performance characteristics of the aerodynamic parachute decelerator devices considered are based on analysis and prior test results for similar configurations and are assumed to be maintained at the scale requirements of the present problem.

Platform C North Installation

NASA Image and Video Library

2016-11-10

A heavy-lift crane lifts the second half of the C-level work platforms, C north, for NASA’s Space Launch System (SLS) rocket, high up from the transfer aisle of the Vehicle Assembly Building (VAB) at NASA's Kennedy Space Center in Florida. The C platform will be moved into High Bay 3 for installation on the north side of High Bay 3. The C platforms are the eighth of 10 levels of work platforms that will surround and provide access to the SLS rocket and Orion spacecraft for Exploration Mission 1. In view below Platform C are several of the previously installed platforms. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to VAB High Bay 3, including installation of the new work platforms, to prepare for NASA’s Journey to Mars.

Geostationary platform systems concepts definition study. Volume 2: Technical, book 3

NASA Technical Reports Server (NTRS)

1980-01-01

The supporting research and technology, and space demonstrations required to support the 1990s operational geostationary platforms are identified. Also the requirements on and interfaces with the Space Transportation System hardware elements supporting the geostationary platform program, including the shuttle, orbital transfer vehicles, teleoperator, etc., are investigated to provide integrated support requirements. Finally, a preliminary evaluation of the practicability and capabilities of an experimental platform from the standpoint of technology, schedule, and cost is given.

Kodak Mirror Assembly Tested at Marshall Space Flight Center

NASA Technical Reports Server (NTRS)

2003-01-01

The Eastman-Kodak mirror assembly is being tested for the James Webb Space Telescope (JWST) project at the X-Ray Calibration Facility at Marshall Space Flight Center (MSFC). In this photo, an MSFC employee is inspecting one of many segments of the mirror assembly for flaws. MSFC is supporting Goddard Space Flight Center (GSFC) in developing the JWST by taking numerous measurements to predict its future performance. The tests are conducted in a vacuum chamber cooled to approximate the super cold temperatures found in space. During its 27 years of operation, the facility has performed testing in support of a wide array of projects, including the Hubble Space Telescope (HST), Solar A, Chandra technology development, Chandra High Resolution Mirror Assembly and science instruments, Constellation X-Ray Mission, and Solar X-Ray Imager, currently operating on a Geostationary Operational Environment Satellite. The JWST is NASA's next generation space telescope, a successor to the Hubble Space Telescope, named in honor of NASA's second administrator, James E. Webb. It is scheduled for launch in 2010 aboard an expendable launch vehicle. It will take about 3 months for the spacecraft to reach its destination, an orbit of 940,000 miles in space.

Kodak Mirror Assembly Tested at Marshall Space Flight Center

NASA Technical Reports Server (NTRS)

2003-01-01

This photo (a frontal view) is of one of many segments of the Eastman-Kodak mirror assembly being tested for the James Webb Space Telescope (JWST) project at the X-Ray Calibration Facility at Marshall Space Flight Center (MSFC). MSFC is supporting Goddard Space Flight Center (GSFC) in developing the JWST by taking numerous measurements to predict its future performance. The tests are conducted in a vacuum chamber cooled to approximate the super cold temperatures found in space. During its 27 years of operation, the facility has performed testing in support of a wide array of projects, including the Hubble Space Telescope (HST), Solar A, Chandra technology development, Chandra High Resolution Mirror Assembly and science instruments, Constellation X-Ray Mission, and Solar X-Ray Imager, currently operating on a Geostationary Operational Environment Satellite. The JWST is NASA's next generation space telescope, a successor to the Hubble Space Telescope, named in honor of NASA's second administrator, James E. Webb. It is scheduled for launch in 2010 aboard an expendable launch vehicle. It will take about 3 months for the spacecraft to reach its destination, an orbit of 940,000 miles in space.

Kodak Mirror Assembly Tested at Marshall Space Flight Center

NASA Technical Reports Server (NTRS)

2003-01-01

This photo (a side view) is of one of many segments of the Eastman-Kodak mirror assembly being tested for the James Webb Space Telescope (JWST) project at the X-Ray Calibration Facility at Marshall Space Flight Center (MSFC). MSFC is supporting Goddard Space Flight Center (GSFC) in developing the JWST by taking numerous measurements to predict its future performance. The tests are conducted in a vacuum chamber cooled to approximate the super cold temperatures found in space. During its 27 years of operation, the facility has performed testing in support of a wide array of projects, including the Hubble Space Telescope (HST), Solar A, Chandra technology development, Chandra High Resolution Mirror Assembly and science instruments, Constellation X-Ray Mission, and Solar X-Ray Imager, currently operating on a Geostationary Operational Environment Satellite. The JWST is NASA's next generation space telescope, a successor to the Hubble Space Telescope, named in honor of NASA's second administrator, James E. Webb. It is scheduled for launch in 2010 aboard an expendable launch vehicle. It will take about 3 months for the spacecraft to reach its destination, an orbit of 940,000 miles in space.

Space Science

NASA Image and Video Library

2003-04-09

The Eastman-Kodak mirror assembly is being tested for the James Webb Space Telescope (JWST) project at the X-Ray Calibration Facility at Marshall Space Flight Center (MSFC). In this photo, an MSFC employee is inspecting one of many segments of the mirror assembly for flaws. MSFC is supporting Goddard Space Flight Center (GSFC) in developing the JWST by taking numerous measurements to predict its future performance. The tests are conducted in a vacuum chamber cooled to approximate the super cold temperatures found in space. During its 27 years of operation, the facility has performed testing in support of a wide array of projects, including the Hubble Space Telescope (HST), Solar A, Chandra technology development, Chandra High Resolution Mirror Assembly and science instruments, Constellation X-Ray Mission, and Solar X-Ray Imager, currently operating on a Geostationary Operational Environment Satellite. The JWST is NASA's next generation space telescope, a successor to the Hubble Space Telescope, named in honor of NASA's second administrator, James E. Webb. It is scheduled for launch in 2010 aboard an expendable launch vehicle. It will take about 3 months for the spacecraft to reach its destination, an orbit of 940,000 miles in space.

Space Science

NASA Image and Video Library

2003-04-09

The Eastman-Kodak mirror assembly is being tested for the James Webb Space Telescope (JWST) project at the X-Ray Calibration Facility at Marshall Space Flight Center (MSFC). In this photo, one of many segments of the mirror assembly is being set up inside the 24-ft vacuum chamber where it will undergo x-ray calibration tests. MSFC is supporting Goddard Space Flight Center (GSFC) in developing the JWST by taking numerous measurements to predict its future performance. The tests are conducted in a vacuum chamber cooled to approximate the super cold temperatures found in space. During its 27 years of operation, the facility has performed testing in support of a wide array of projects, including the Hubble Space Telescope (HST), Solar A, Chandra technology development, Chandra High Resolution Mirror Assembly and science instruments, Constellation X-Ray Mission, and Solar X-Ray Imager, currently operating on a Geostationary Operational Environment Satellite. The JWST is NASA's next generation space telescope, a successor to the Hubble Space Telescope, named in honor of NASA's second administrator, James E. Webb. It is scheduled for launch in 2010 aboard an expendable launch vehicle. It will take about 3 months for the spacecraft to reach its destination, an orbit of 940,000 miles in space.

Platform C North Installation

NASA Image and Video Library

2016-11-10

A heavy-lift crane lowers the second half of the C-level work platforms, C north, for NASA’s Space Launch System (SLS) rocket, into High Bay 3 of the Vehicle Assembly Building (VAB) at NASA's Kennedy Space Center in Florida. The C platform will be installed on the north side of High Bay 3. In view below are several of the previously installed levels of platforms. The C platforms are the eighth of 10 levels of work platforms that will surround and provide access to the SLS rocket and Orion spacecraft for Exploration Mission 1. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to VAB High Bay 3, including installation of the new work platforms, to prepare for NASA’s Journey to Mars.

KENNEDY SPACE CENTER, FLA. - This bird's-eye view of a high bay in the Orbiter Processing Facility (OPF) shows Space Shuttle Atlantis surrounded by the standard platforms and equipment required to process a Space Shuttle orbiter for flight. The high bay is 197 feet (60 meters) long, 150 feet (46 meters) wide, 95 feet (29 meters) high, and encompasses a 29,000-square-foot (2,694-meter) area. Platforms, a main access bridge, and two rolling bridges with trucks provide access to various parts of the orbiter. The next mission scheduled for Atlantis is STS-114, a utilization and logistics flight to the International Space Station.

NASA Image and Video Library

2003-09-03

KENNEDY SPACE CENTER, FLA. - This bird's-eye view of a high bay in the Orbiter Processing Facility (OPF) shows Space Shuttle Atlantis surrounded by the standard platforms and equipment required to process a Space Shuttle orbiter for flight. The high bay is 197 feet (60 meters) long, 150 feet (46 meters) wide, 95 feet (29 meters) high, and encompasses a 29,000-square-foot (2,694-meter) area. Platforms, a main access bridge, and two rolling bridges with trucks provide access to various parts of the orbiter. The next mission scheduled for Atlantis is STS-114, a utilization and logistics flight to the International Space Station.

Ariane Transfer Vehicle in service of man in orbit

NASA Astrophysics Data System (ADS)

Deutscher, N.; Schefold, K.; Cougnet, C.

1988-10-01

The Ariane Transfer Vehicle (ATV), an unmanned propulsion system that is designed to be carried by the Ariane 5 launch vehicle, will undertake the logistical support required by the International Space Station and the Man-Tended Free Flyer, carrying both pressurized and unpressurized cargo to these spacecraft and carrying away wastes. The ATV is an expendable vehicle, disposed of by burn-up during reentry, and will be available for initial operations in 1996. In order to minimize development costs and recurrent costs, the ATV design will incorporate existing hardware and software.

Proceedings of the 4th Conference on Aerospace Materials, Processes, and Environmental Technology

NASA Technical Reports Server (NTRS)

Griffin, D. E. (Editor); Stanley, D. C. (Editor)

2001-01-01

The next millennium challenges us to produce innovative materials, processes, manufacturing, and environmental technologies that meet low-cost aerospace transportation needs while maintaining US leadership. The pursuit of advanced aerospace materials, manufacturing processes, and environmental technologies supports the development of safer, operational, next-generation, reusable, and expendable aeronautical and space vehicle systems. The Aerospace Materials, Processes, and Environmental Technology Conference (AMPET) provided a forum for manufacturing, environmental, materials, and processes engineers, scientists, and managers to describe, review, and critically assess advances in these key technology areas.

Earth Science

NASA Image and Video Library

1995-12-01

The reflection of the Atlas IIAS expendable launch vehicle with the Solar Heliospheric Observatory (SOHO) inside its payload fairing can be seen on the surface of a retention pond at Launch Pad 36B on Cape Canaveral Air Station just hours before liftoff. SOHO is a cooperative effort involving NASA and the European Space Agency (ESA) within the framework of the International Solar-Terrestrial Physics Program. During its 2-year mission, the SOHO spacecraft will gather data on the internal structure of the Sun, its extensive outer atmosphere and the origin of the solar wind.

Vibroacoustic Payload Environment Prediction System (VAPEPS): VAPEPS management center remote access guide

NASA Technical Reports Server (NTRS)

Fernandez, J. P.; Mills, D.

1991-01-01

A Vibroacoustic Payload Environment Prediction System (VAPEPS) Management Center was established at the JPL. The center utilizes the VAPEPS software package to manage a data base of Space Shuttle and expendable launch vehicle payload flight and ground test data. Remote terminal access over telephone lines to the computer system, where the program resides, was established to provide the payload community a convenient means of querying the global VAPEPS data base. This guide describes the functions of the VAPEPS Management Center and contains instructions for utilizing the resources of the center.

Laboratory prototype flash evaporator

NASA Technical Reports Server (NTRS)

Gaddis, J. L.

1972-01-01

A laboratory prototype flash evaporator that is being developed as a candidate for the space shuttle environmental control system expendable heat sink is described. The single evaporator configuration uses water as an evaporant to accommodate reentry and on-orbit peak heat loads, and Freon 22 for terrestrial flight phases below 120,000 feet altitude. The design features, fabrication techniques used for the prototype unit, redundancy considerations, and the fluid temperature control arrangement are reported in detail. The results of an extensive test program to determine the evaporator operational characteristics under a wide variety of conditions are presented.

Historical problem areas: Lessons learned for expendable and reusable vehicle propulsion systems

NASA Technical Reports Server (NTRS)

Fester, Dale A.

1991-01-01

The following subject areas are covered: expendable launch vehicle lessons learned, upper stage/transfer vehicle lessons learned, shuttle systems - reuse, and reusable system issues and lessons learned.

KSC-97PC1094

NASA Image and Video Library

1997-07-19

Jet Propulsion Laboratory (JPL) employees bolt a radioisotope thermoelectric generator (RTG) onto the Cassini spacecraft, at left, while other JPL workers, at right, operate the installation cart on a raised platform in the Payload Hazardous Servicing Facility (PHSF). Cassini will be outfitted with three RTGs. The power units are undergoing mechanical and electrical verification tests in the PHSF. The RTGs will provide electrical power to Cassini on its 6.7-year trip to the Saturnian system and during its four-year mission at Saturn. RTGs use heat from the natural decay of plutonium to generate electric power. The generators enable spacecraft to operate at great distances from the Sun where solar power systems are not feasible. The Cassini mission is targeted for an Oct. 6 launch aboard a Titan IVB/Centaur expendable launch vehicle. Cassini is built and managed by JPL

Cassini's RTGs undergo mechanical and electrical verification testing in the PHSF

NASA Technical Reports Server (NTRS)

1997-01-01

Jet Propulsion Laboratory (JPL) workers carefully roll into place a platform with a second radioisotope thermoelectric generator (RTG) for installation on the Cassini spacecraft. In background at left, the first of three RTGs already has been installed on Cassini. The RTGs will provide electrical power to Cassini on its 6.7-year trip to the Saturnian system and during its four-year mission at Saturn. The power units are undergoing mechanical and electrical verification testing in the Payload Hazardous Servicing Facility. RTGs use heat from the natural decay of plutonium to generate electric power. The generators enable spacecraft to operate far from the Sun where solar power systems are not feasible. The Cassini mission is scheduled for an Oct. 6 launch aboard a Titan IVB/Centaur expendable launch vehicle. Cassini is built and managed for NASA by JPL.

HyperForest: A high performance multi-processor architecture for real-time intelligent systems

DOE Office of Scientific and Technical Information (OSTI.GOV)

Garcia, P. Jr.; Rebeil, J.P.; Pollard, H.

1997-04-01

Intelligent Systems are characterized by the intensive use of computer power. The computer revolution of the last few years is what has made possible the development of the first generation of Intelligent Systems. Software for second generation Intelligent Systems will be more complex and will require more powerful computing engines in order to meet real-time constraints imposed by new robots, sensors, and applications. A multiprocessor architecture was developed that merges the advantages of message-passing and shared-memory structures: expendability and real-time compliance. The HyperForest architecture will provide an expandable real-time computing platform for computationally intensive Intelligent Systems and open the doorsmore » for the application of these systems to more complex tasks in environmental restoration and cleanup projects, flexible manufacturing systems, and DOE`s own production and disassembly activities.« less

Earth resources instrumentation for the Space Station Polar Platform

NASA Technical Reports Server (NTRS)

Donohoe, Martin J.; Vane, Deborah

1986-01-01

The spacecraft and payloads of the Space Station Polar Platform program are described in a brief overview. Present plans call for one platform in a descending morning-equator-crossing orbit at 824 km and two or three platforms in ascending afternoon-crossing orbits at 542-824 km. The components of the NASA Earth Observing System (EOS) and NOAA payloads are listed in tables and briefly characterized, and data-distribution requirements and the mission development schedule are discussed. A drawing of the platform, a graph showing the spectral coverage of the EOS instruments, and a glossary of acronyms are provided.

Control system design for the large space systems technology reference platform

NASA Technical Reports Server (NTRS)

Edmunds, R. S.

1982-01-01

Structural models and classical frequency domain control system designs were developed for the large space systems technology (LSST) reference platform which consists of a central bus structure, solar panels, and platform arms on which a variety of experiments may be mounted. It is shown that operation of multiple independently articulated payloads on a single platform presents major problems when subarc second pointing stability is required. Experiment compatibility will be an important operational consideration for systems of this type.

Platform C Installation

NASA Image and Video Library

2016-10-19

A heavy-lift crane lifts the first half of the C-level work platforms, C south, for NASA’s Space Launch System (SLS) rocket, high up from the transfer aisle floor of the Vehicle Assembly Building (VAB) at NASA’s Kennedy Space Center in Florida. The C platform will be installed on the south side of High Bay 3. The C platforms are the eighth of 10 levels of work platforms that will surround and provide access to the SLS rocket and Orion spacecraft for Exploration Mission 1. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to VAB High Bay 3, including installation of the new work platforms, to prepare for NASA’s Journey to Mars.

Platform C North Installation

NASA Image and Video Library

2016-11-10

A heavy-lift crane lifts the second half of the C-level work platforms, C north, for NASA’s Space Launch System (SLS) rocket, high up from the transfer aisle floor of the Vehicle Assembly Building (VAB) at NASA’s Kennedy Space Center in Florida. The C platform will be installed on the north side of High Bay 3. The C platforms are the eighth of 10 levels of work platforms that will surround and provide access to the SLS rocket and Orion spacecraft for Exploration Mission 1. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to VAB High Bay 3, including installation of the new work platforms, to prepare for NASA’s Journey to Mars.

Platform C Installation

NASA Image and Video Library

2016-10-19

A heavy-lift crane lifts the first half of the C-level work platforms, C south, for NASA’s Space Launch System (SLS) rocket, high up from the transfer aisle floor of the Vehicle Assembly Building (VAB) at NASA’s Kennedy Space Center in Florida. The C platform will be moved into High Bay 3 for installation on the south wall. The C platforms are the eighth of 10 levels of work platforms that will surround and provide access to the SLS rocket and Orion spacecraft for Exploration Mission 1. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to VAB High Bay 3, including installation of the new work platforms, to prepare for NASA’s Journey to Mars.

Platform C Installation

NASA Image and Video Library

2016-10-19

Inside the Vehicle Assembly Building at NASA’s Kennedy Space Center in Florida, a construction worker assist with the installation of the first half of the C-level work platforms, C south, for NASA’s Space Launch System (SLS) rocket. The large bolts that hold the platform in place on the south wall are being secured. The C platforms are the eighth of 10 levels of work platforms that will surround and provide access to the SLS rocket and Orion spacecraft for Exploration Mission 1. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to VAB High Bay 3, including installation of the new work platforms, to prepare for NASA’s Journey to Mars.

Platform C North Installation

NASA Image and Video Library

2016-11-10

A heavy-lift crane lifts the second half of the C-level work platforms, C north, for NASA’s Space Launch System (SLS) rocket, up from the transfer aisle floor of the Vehicle Assembly Building (VAB) at NASA’s Kennedy Space Center in Florida. The C platform will be installed on the north side of High Bay 3. The C platforms are the eighth of 10 levels of work platforms that will surround and provide access to the SLS rocket and Orion spacecraft for Exploration Mission 1. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to VAB High Bay 3, including installation of the new work platforms, to prepare for NASA’s Journey to Mars.

Platform C North Installation

NASA Image and Video Library

2016-11-10

A heavy-lift crane lifts the second half of the C-level work platforms, C north, for NASA’s Space Launch System (SLS) rocket, high up from the transfer aisle floor of the Vehicle Assembly Building (VAB) at NASA’s Kennedy Space Center in Florida. The C platform will be moved into High Bay 3 for installation on the north wall. The C platforms are the eighth of 10 levels of work platforms that will surround and provide access to the SLS rocket and Orion spacecraft for Exploration Mission 1. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to VAB High Bay 3, including installation of the new work platforms, to prepare for NASA’s Journey to Mars.

KSC-06pd1285

NASA Image and Video Library

2006-06-28

KENNEDY SPACE CENTER, FLA. - At the Cape Canaveral forecast facility in Florida, media were able to meet members of the weather team who review data used for forecasts as part of a tour of the facility. The team will play a role in the July 1 launch of Space Shuttle Discovery on mission STS-121. At the facility, which is operated by the U.S. Air Force 45th Weather Squadron, received a briefing on how the launch weather forecast is developed by Shuttle Weather Officer Kathy Winters and met the forecasters for the space shuttle and the expendable launch vehicles. Also participating were members of the Applied Meteorology Unit who provide special expertise to the forecasters by analyzing and interpreting unusual or inconsistent weather data. The media were able to see the release of the Rawinsonde weather balloon carrying instruments aloft to be used as part of developing the forecast. Photo credit: NASA/George Shelton

Utilizing Advanced Vibration Isolation Technology to Enable Microgravity Science Operations

NASA Technical Reports Server (NTRS)

Alhorn, Dean Carl

1999-01-01

Microgravity scientific research is performed in space to determine the effects of gravity upon experiments. Until recently, experiments had to accept the environment aboard various carriers: reduced-gravity aircraft, sub-orbital payloads, Space Shuttle, and Mir. If the environment is unacceptable, then most scientists would rather not expend the resources without the assurance of true microgravity conditions. This is currently the case on the International Space Station, because the ambient acceleration environment will exceed desirable levels. For this reason, the g-LIMIT (Glovebox Integrated Microgravity Isolation Technology) system is currently being developed to provide a quiescent acceleration environment for scientific operations. This sub-rack isolation system will provide a generic interface for a variety of experiments for the Microgravity Science Glovebox. This paper describes the motivation for developing of the g-LIMIT system, presents the design concept and details some of the advanced technologies utilized in the g-LIMIT flight design.

Low thrust vehicle concept study

NASA Technical Reports Server (NTRS)

1980-01-01

Low thrust chemical (hydrogen-oxygen) propulsion systems configured specifically for low acceleration orbit transfer of large space systems were defined. Results indicate that it is cost effective and least risk to combine the OTV and stowed spacecraft in a single 65 K Shuttle. The study shows that the engine for an optimized low thrust stage (1) does not require very low thrust; (2) 1-3 K thrust range appears optimum; (3) thrust transient is not a concern; (4) throttling probably not worthwhile; and (5) multiple thrusters complicate OTV/LSS design and aggravate LSS loads. Regarding the optimum vehicle for low acceleration missions, the single shuttle launch (LSS and expendable OTV) is most cost effective and least risky. Multiple shuttles increase diameter 20%. The space based radar structure short OTV (which maximizes space available for packaged LSS) favors use of torus tank. Propellant tank pressures/vapor residuals are little affected by engine thrust level or number of burns.

Materials samples face rigors of space.

PubMed

Flinn, Edward D

2002-07-01

The Materials International Space Station Experiment (MISSE) is described. This project is designed to conduct long duration materials tests on samples attached to the ISS. A batch of 750 material samples were delivered on STS-105 and attached to the ISS airlock. They will be exposed to the space environment for 18 months and are slated to return on STS-114. A second batch of 750 samples is being prepared. The experiment containers were used originally for the Mir Environmental Effects Payload, which tested a variety of substances, including some slated for use on the ISS. Researchers are particularly interested in the effects of atomic oxygen on the samples. Some samples are being tested to determine their use in radiation protection. As part of the MISSE project, ultrathin tether materials are being tested for use on the Propulsive Small Expendable Depoloyer System (ProSEDS), which will use a tether system to change a satellite's orbital altitude.

Blade platform seal for ceramic/metal rotor assembly

DOEpatents

Wertz, John L.

1982-01-01

A combination ceramic and metal turbine rotor for use in high temperature gas turbine engines includes a metal rotor disc having a rim with a plurality of circumferentially spaced blade root retention slots therein to receive a plurality of ceramic blades, each including side platform segments thereon and a dovetail configured root slidably received in one of the slots. Adjacent ones of the platform segments including edge portions thereon closely spaced when the blades are assembled to form expansion gaps in an annular flow surface for gas passage through the blades and wherein the assembly further includes a plurality of unitary seal members on the rotor connected to its rim and each including a plurality of spaced, axially extending, flexible fingers that underlie and conform to the edge portions of the platform segments and which are operative at turbine operating temperatures and speeds to distribute loading on the platform segments as the fingers are seated against the underside of the blade platforms to seal the gaps without undesirably stressing thin web ceramic sections of the platform.

Reconfigurable, Intelligently-Adaptive, Communication System, an SDR Platform

NASA Technical Reports Server (NTRS)

Roche, Rigoberto

2016-01-01

The Space Telecommunications Radio System (STRS) provides a common, consistent framework to abstract the application software from the radio platform hardware. STRS aims to reduce the cost and risk of using complex, configurable and reprogrammable radio systems across NASA missions. The Glenn Research Center (GRC) team made a software-defined radio (SDR) platform STRS compliant by adding an STRS operating environment and a field programmable gate array (FPGA) wrapper, capable of implementing each of the platforms interfaces, as well as a test waveform to exercise those interfaces. This effort serves to provide a framework toward waveform development on an STRS compliant platform to support future space communication systems for advanced exploration missions. Validated STRS compliant applications provided tested code with extensive documentation to potentially reduce risk, cost and efforts in development of space-deployable SDRs. This paper discusses the advantages of STRS, the integration of STRS onto a Reconfigurable, Intelligently-Adaptive, Communication System (RIACS) SDR platform, the sample waveform, and wrapper development efforts. The paper emphasizes the infusion of the STRS Architecture onto the RIACS platform for potential use in next generation SDRs for advance exploration missions.

The Wake Shield Facility: A space experiment platform

NASA Technical Reports Server (NTRS)

Allen, Joseph P.

1991-01-01

Information is given in viewgraph form on Wakeshield, a space experiment platform. The Wake Shield Facility (WSF) flight program objectives, product applications, commercial development approach, and cooperative experiments are listed. The program objectives are to produce new industry-driven electronic, magnetic, and superconducting thin-film materials and devices both in terrestrial laboratories and in space; utilize the ultra-vacuum of space for thin film epitaxial growth and materials processing; and develop commercial space hardware for research and development and enhanced access to space.

Thin film microelectronics materials production in the vacuum of space

NASA Astrophysics Data System (ADS)

Ignatiev, A.; Sterling, M.; Horton, C.; Freundlich, A.; Pei, S.; Hill, R.

1997-01-01

The international Space Station era will open up a new dimension in the use of one of the unique attributes of space, vacuum, for the production of advanced semiconductor materials and devices for microelectronics applications. Ultra-vacuum is required for the fabrication in thin film form of high quality semiconductors. This can be accomplished behind a free flying platform similar to the current Wake Shield Facility which is specifically designed to support in-space production. The platform will require apparatus for thin film growth, a robotics interface to allow for the change out of raw materials and the harvesting of finished product, and a servicing plant incorporating Space Station that will support long-term utilization of the platform.

Space environmental effects on materials

NASA Technical Reports Server (NTRS)

Schwinghmaer, R. J.

1980-01-01

The design of long life platforms and structures for space is discussed in terms of the space environmental effects on the materials used. Vacuum, ultraviolet radiation, and charged particle radiation are among the factors considered. Research oriented toward the acquisition of long term environmental effects data needed to support the design and development of large low Earth orbit and geosynchronous Earth orbit space platforms and systems is described.

Business Context of Space Tourism

NASA Astrophysics Data System (ADS)

Schmitt, Harrison H.

2003-01-01

Broadly speaking, two types of potential commercial activity in space can be defined. First, there are those activities that represent an expansion and improvement on services with broad existing commercial foundations such as telecommunications. The second type of potential commercial activity in space is one that may offer a type of service with few or any existing commercial foundations such as space-based remote sensing. Space tourism clearly belongs in the first category of potential commercial activity in space. Roles in cooperation with the private sector that might be considered for NASA include 1) acceleration of the ``Professional-in Space'' initiative, 2) research and technology developments related to a) a ``Tourist Destination Module'' for the Space Station, b) an ``Extra Passengers Module'' for the payload bay of the Space Shuttle, and c) a ``Passenger-rated Expendable Launch Vehicle,'' 3) definition of criteria for qualifying candidate space tourists, and 4) initiatives to protect space tourism from unreasonable tort litigation. As baseline information for establishing fees, the cost of a possible tourist flight should be fully and objectively delineated. If it is correct that the marginal cost of each Space Shuttle flight to Earth-orbit is about $100 million and the effective Shuttle payload is about 50,000 pounds, then the marginal cost would be roughly $2,000 per pound.

Technical issues in the conduct of large space platform experiments in plasma physics and geoplasma sciences

NASA Technical Reports Server (NTRS)

Szuszczewicz, Edward P.

1986-01-01

Large, permanently-manned space platforms can provide exciting opportunities for discoveries in basic plasma and geoplasma sciences. The potential for these discoveries will depend very critically on the properties of the platform, its subsystems, and their abilities to fulfill a spectrum of scientific requirements. With this in mind, the planning of space station research initiatives and the development of attendant platform engineering should allow for the identification of critical science and technology issues that must be clarified far in advance of space station program implementation. An attempt is made to contribute to that process, with a perspective that looks to the development of the space station as a permanently-manned Spaceborne Ionospheric Weather Station. The development of this concept requires a synergism of science and technology which leads to several critical design issues. To explore the identification of these issues, the development of the concept of an Ionospheric Weather Station will necessarily touch upon a number of diverse areas. These areas are discussed.

Occupational dreams, choices and aspirations: adolescents' entrepreneurial prospects and orientations.

PubMed

Schmitt-Rodermund, Eva; Vondracek, Fred W

2002-02-01

The present study examined possible early antecedents of entrepreneurship of 14-17-year-old 10th grade students (n=320). We hypothesized that Entrepreneurial Orientation (interest and self-efficacy), together with Willingness to Expend Effort, would be an important predictor of an adolescent's Entrepreneurial Prospects, i.e. prospects of becoming self-employed in the future. Furthermore, personality and the model of self-employed family were expected to predict the level of Entrepreneurial Orientation. The same relationships were investigated separately for students who were more or less willing to expend effort. Among students more willing to expend effort, levels of Entrepreneurial Orientation were higher for those who were conscientious, self-efficient, open to new experiences, and low in agreeableness. Among students less willing to expend effort, a high need for social recognition predicted higher levels of Entrepreneurial Orientation. In addition, parents' model for them was connected with lower levels of Entrepreneurial Orientation. A moderating effect of Willingness to Expend Effort was supported by the results for parents' model and need for social recognition. Copyright 2002 Published by Elsevier Science Ltd on behalf of The Association for Professionals in Services for Adolescents.

Chromatography process development in the quality by design paradigm I: Establishing a high-throughput process development platform as a tool for estimating "characterization space" for an ion exchange chromatography step.

PubMed

Bhambure, R; Rathore, A S

2013-01-01

This article describes the development of a high-throughput process development (HTPD) platform for developing chromatography steps. An assessment of the platform as a tool for establishing the "characterization space" for an ion exchange chromatography step has been performed by using design of experiments. Case studies involving use of a biotech therapeutic, granulocyte colony-stimulating factor have been used to demonstrate the performance of the platform. We discuss the various challenges that arise when working at such small volumes along with the solutions that we propose to alleviate these challenges to make the HTPD data suitable for empirical modeling. Further, we have also validated the scalability of this platform by comparing the results from the HTPD platform (2 and 6 μL resin volumes) against those obtained at the traditional laboratory scale (resin volume, 0.5 mL). We find that after integration of the proposed correction factors, the HTPD platform is capable of performing the process optimization studies at 170-fold higher productivity. The platform is capable of providing semi-quantitative assessment of the effects of the various input parameters under consideration. We think that platform such as the one presented is an excellent tool for examining the "characterization space" and reducing the extensive experimentation at the traditional lab scale that is otherwise required for establishing the "design space." Thus, this platform will specifically aid in successful implementation of quality by design in biotech process development. This is especially significant in view of the constraints with respect to time and resources that the biopharma industry faces today. Copyright © 2013 American Institute of Chemical Engineers.

Experiment module concepts study. Volume 1: Management summary

NASA Technical Reports Server (NTRS)

1970-01-01

The minimum number of standardized (common) module concepts that will satisfy the experiment program for manned space stations at least cost is investigated. The module interfaces with other elements such as the space shuttle, ground stations, and the experiments themselves are defined. The total experiment module program resource and test requirements are also considered. The minimum number of common module concepts that will satisfy the program at least cost is found to be three, plus a propulsion slice and certain experiment-peculiar integration hardware. The experiment modules rely on the space station for operational, maintenance, and logistic support. They are compatible with both expendable and shuttle launch vehicles, and with servicing by shuttle, tug, or directly from the space station. A total experiment module program cost of approximately $2319M under the study assumptions is indicated. This total is made up of $838M for experiment module development and production, $806M for experiment equipment, and $675M for interface hardware, experiment integration, launch and flight operations, and program management and support.

Avionic architecture requirements for Space Exploration Initiative systems

NASA Technical Reports Server (NTRS)

Herbella, C. G.; Brown, D. C.

1991-01-01

The authors discuss NASA's Strategic Avionics Technology Working Group (SATWG) and the results of the first study commissioned by the SATWG, the Space Avionics Requirements Study (SARS). The goal of the SARS task was to show that an open avionics architecture, using modular, standardized components, could be applied across the wide range of systems that comprise the Space Exploration Initiative. The study addressed systems ranging from expendable launch vehicles and the space station to surface systems such as Mars or lunar rovers and habitats. Top-level avionics requirements were derived from characterizations of each of the systems considered. Then a set of avionics subsystems were identified, along with estimates of the numbers and types of modules needed to meet the requirements. Applicability of these results across the infrastructure was then illustrated. In addition to these tasks, critical technologies were identified, characterized, and assessed in terms of their criticality and impact on the program. Design, development, test, and evaluation methods were addressed to identify potential areas of improvement.

Vulnerability assessment of a space based weapon platform electronic system exposed to a thermonuclear weapon detonation

NASA Astrophysics Data System (ADS)

Perez, C. L.; Johnson, J. O.

Rapidly changing world events, the increased number of nations with inter-continental ballistic missile capability, and the proliferation of nuclear weapon technology will increase the number of nuclear threats facing the world today. Monitoring these nation's activities and providing an early warning and/or intercept system via reconnaissance and surveillance satellites and space based weapon platforms is a viable deterrent against a surprise nuclear attack. However, the deployment of satellite and weapon platform assets in space will subject the sensitive electronic equipment to a variety of natural and man-made radiation environments. These include Van Allen Belt protons and electrons; galactic and solar flare protons; and neutrons, gamma rays, and x-rays from intentionally detonated fission and fusion weapons. In this paper, the MASH vl.0 code system is used to estimate the dose to the critical electronics components of an idealized space based weapon platform from neutron and gamma-ray radiation emitted from a thermonuclear weapon detonation in space. Fluence and dose assessments were performed for the platform fully loaded, and in several stages representing limited engagement scenarios. The results indicate vulnerabilities to the Command, Control, and Communication bay instruments from radiation damage for a nuclear weapon detonation for certain source/platform orientations. The distance at which damage occurs will depend on the weapon yield (n,(gamma)/kiloton) and size (kilotons).

Learning to build large structures in space

NASA Technical Reports Server (NTRS)

Hagler, T.; Patterson, H. G.; Nathan, C. A.

1977-01-01

The paper examines some of the key technologies and forms of construction know-how that will have to be developed and tested for eventual application to building large structures in space. Construction of a shuttle-tended space construction/demonstration platform would comprehensively demonstrate large structure technology, develop construction capability, and furnish a construction platform for a variety of operational large structures. Completion of this platform would lead to demonstrations of the Satellite Power System (SPS) concept, including microwave transmission, fabrication of 20-m-deep beams, conductor installation, rotary joint installation, and solar blanket installation.

Future Launch Vehicle Structures - Expendable and Reusable Elements

NASA Astrophysics Data System (ADS)

Obersteiner, M. H.; Borriello, G.

2002-01-01

Further evolution of existing expendable launch vehicles will be an obvious element influencing the future of space transportation. Besides this reusability might be the change with highest potential for essential improvement. The expected cost reduction and finally contributing to this, the improvement of reliability including safe mission abort capability are driving this idea. Although there are ideas of semi-reusable launch vehicles, typically two stages vehicles - reusable first stage or booster(s) and expendable second or upper stage - it should be kept in mind that the benefit of reusability will only overwhelm if there is a big enough share influencing the cost calculation. Today there is the understanding that additional technology preparation and verification will be necessary to master reusability and get enough benefits compared with existing launch vehicles. This understanding is based on several technology and system concepts preparation and verification programmes mainly done in the US but partially also in Europe and Japan. The major areas of necessary further activities are: - System concepts including business plan considerations - Sub-system or component technologies refinement - System design and operation know-how and capabilities - Verification and demonstration oriented towards future mission mastering: One of the most important aspects for the creation of those coming programmes and activities will be the iterative process of requirements definition derived from concepts analyses including economical considerations and the results achieved and verified within technology and verification programmes. It is the intention of this paper to provide major trends for those requirements focused on future launch vehicles structures. This will include the aspects of requirements only valid for reusable launch vehicles and those common for expendable, semi-reusable and reusable launch vehicles. Structures and materials is and will be one of the important technology areas to be improved. This includes: - Primary structures - Thermal protection systems (for high and low temperatures) - Hot structures (leading edges, engine cowling, ...) - Tanks (for various propellants and fluids, cryo, ...) Requirements to be considered are including materials properties and a variety of loads definition - static and dynamic. Based on existing knowledge and experience for expendable LV (Ariane, ...) and aircraft there is the need to established a combined understanding to provide the basis for an efficient RLV design. Health monitoring will support the cost efficient operation of future reusable structures, but will also need a sound understanding of loads and failure mechanisms as basis. Risk mitigation will ask for several steps of demonstration towards a cost efficient RLV (structures) operation. Typically this has or will start with basic technology, to be evolved to components demonstration (TPS, tanks, ...) and finally to result in the demonstration of the cost efficient reuse operation. This paper will also include a programmatic logic concerning future LV structures demonstration.

Platform C Installation

NASA Image and Video Library

2016-10-19

A heavy-lift crane lifts the first half of the C-level work platforms, C south, for NASA’s Space Launch System (SLS) rocket, up from the transfer aisle floor of the Vehicle Assembly Building (VAB) at NASA’s Kennedy Space Center in Florida. Large Tandemloc bars have been attached to the platform to keep it level during lifting and installation. The C platform will be installed on the south side of High Bay 3. The C platforms are the eighth of 10 levels of work platforms that will surround and provide access to the SLS rocket and Orion spacecraft for Exploration Mission 1. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to VAB High Bay 3, including installation of the new work platforms, to prepare for NASA’s Journey to Mars.

Cycom 977-2 Composite Material: Impact Test Results (workshop presentation)

NASA Technical Reports Server (NTRS)

Engle, Carl; Herald, Stephen; Watkins, Casey

2005-01-01

Contents include the following: Ambient (13A) tests of Cycom 977-2 impact characteristics by the Brucenton and statistical method at MSFC and WSTF. Repeat (13A) tests of tested Cycom from phase I at MSFC to expended testing statistical database. Conduct high-pressure tests (13B) in liquid oxygen (LOX) and GOX at MSFC and WSTF to determine Cycom reaction characteristics and batch effect. Conduct expended ambient (13A) LOX test at MSFC and high-pressure (13B) testing to determine pressure effects in LOX. Expend 13B GOX database.

An Innovative 6-DOF Platform for Testing a Space Robotic System to Perform Contact Tasks in Zero-Gravity Environment

DTIC Science & Technology

2013-10-21

Platform for Testing a Space Robotic System to Perform Contact Tasks in Zero- Gravity Environment 5a. CONTRACT NUMBER FA9453-11-1-0306 5b...SUBJECT TERMS Microgravity, zero gravity , test platform, simulation, gravity offloading 16. SECURITY CLASSIFICATION OF: 17. LIMITATION OF ABSTRACT...4  3.3  Principle of Gravity Offloading

Technology review: prototyping platforms for monitoring ambient conditions.

PubMed

Afolaranmi, Samuel Olaiya; Ramis Ferrer, Borja; Martinez Lastra, Jose Luis

2018-05-08

The monitoring of ambient conditions in indoor spaces is very essential owing to the amount of time spent indoors. Specifically, the monitoring of air quality is significant because contaminated air affects the health, comfort and productivity of occupants. This research work presents a technology review of prototyping platforms for monitoring ambient conditions in indoor spaces. It involves the research on sensors (for CO 2 , air quality and ambient conditions), IoT platforms, and novel and commercial prototyping platforms. The ultimate objective of this review is to enable the easy identification, selection and utilisation of the technologies best suited for monitoring ambient conditions in indoor spaces. Following the review, it is recommended to use metal oxide sensors, optical sensors and electrochemical sensors for IAQ monitoring (including NDIR sensors for CO 2 monitoring), Raspberry Pi for data processing, ZigBee and Wi-Fi for data communication, and ThingSpeak IoT platform for data storage, analysis and visualisation.

41 CFR 101-26.103-2 - Restriction on personal convenience items.

Code of Federal Regulations, 2012 CFR

2012-07-01

... funds may be expended for pictures, objects of art, plants, or flowers (both artificial and real), or... expended for pictures, objects of art, plants, flowers (both artificial and real), or any other similar...

41 CFR 101-26.103-2 - Restriction on personal convenience items.

Code of Federal Regulations, 2011 CFR

2011-07-01

... funds may be expended for pictures, objects of art, plants, or flowers (both artificial and real), or... expended for pictures, objects of art, plants, flowers (both artificial and real), or any other similar...

41 CFR 101-26.103-2 - Restriction on personal convenience items.

Code of Federal Regulations, 2013 CFR

2013-07-01

... funds may be expended for pictures, objects of art, plants, or flowers (both artificial and real), or... expended for pictures, objects of art, plants, flowers (both artificial and real), or any other similar...

41 CFR 101-26.103-2 - Restriction on personal convenience items.

Code of Federal Regulations, 2014 CFR

2014-07-01

... funds may be expended for pictures, objects of art, plants, or flowers (both artificial and real), or... expended for pictures, objects of art, plants, flowers (both artificial and real), or any other similar...

41 CFR 101-26.103-2 - Restriction on personal convenience items.

Code of Federal Regulations, 2010 CFR

2010-07-01

... funds may be expended for pictures, objects of art, plants, or flowers (both artificial and real), or... expended for pictures, objects of art, plants, flowers (both artificial and real), or any other similar...

Platform C North Arrival

NASA Image and Video Library

2016-08-30

A section of the second half of the C-level platforms, C North, for NASA’s Space Launch System (SLS) rocket, arrives at the agency’s Kennedy Space Center in Florida. The platform was offloaded from a heavy lift transport truck and secured in a staging area in the west parking lot of the Vehicle Assembly Building (VAB). The Ground Systems Development and Operations Program is overseeing upgrades and modifications to VAB High Bay 3 to support processing of the SLS and Orion spacecraft. A total of 10 levels of new platforms, 20 platform halves altogether, will surround the SLS rocket and Orion spacecraft and provide access for testing and processing.

Floor Plans Level 15 Load Platform, Level 17 Lower ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Floor Plans - Level 15 Load Platform, Level 17 Lower Platform, Level 22 and Upper Platform, and Level 27 - Marshall Space Flight Center, Saturn V S-IC Static Test Facility, West Test Area, Huntsville, Madison County, AL

Space assembly fixtures and aids

NASA Technical Reports Server (NTRS)

Bloom, K. A.; Lillenas, A. N.

1980-01-01

Concepts and requirements for assembly fixtures and aids necessary for the assembly and maintenance of spare platforms were studied. Emphasis was placed on erectable and deployable type structures with the shuttle orbiter as the assembly base. Both single and multiple orbiter flight cases for the platform assembly were considered. Applicable space platform assembly studies were reviewed to provide a data base for establishing the assembly fixture and aids design requirements, assembly constraints, and the development of representative design concepts. Conclusions indicated that fixture requirements will vary with platform size. Larger platforms will require translation relative to the orbiter RMS working volume. The installation of platform payloads and subsystems (e.g., utility distribution) must also be considered in the specification of assembly fixtures and aids.

Platform B North Installation

NASA Image and Video Library

2016-12-16

Construction workers wearing safety harnesses and tethered lines assist with the installation of the second half of the B-level work platforms, B north, for NASA’s Space Launch System (SLS) rocket, high up in the Vehicle Assembly Building (VAB) at NASA’s Kennedy Space Center in Florida. They are securing the large bolts that hold the platform securely in place on the north side of High Bay 3. The B platforms are the ninth of 10 levels of work platforms that will surround and provide access to the SLS rocket and Orion spacecraft for Exploration Mission 1. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to VAB High Bay 3, including installation of the new work platforms, to prepare for NASA’s Journey to Mars.

Platform C North Installation

NASA Image and Video Library

2016-11-10

A heavy-lift crane lifts the second half of the C-level work platforms, C north, for NASA’s Space Launch System (SLS) rocket, high up from the transfer aisle of the Vehicle Assembly Building (VAB) at NASA's Kennedy Space Center in Florida. The C platform will be moved into High Bay 3 for installation on the north side of High Bay 3. The C platforms are the eighth of 10 levels of work platforms that will surround and provide access to the SLS rocket and Orion spacecraft for Exploration Mission 1. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to VAB High Bay 3, including installation of the new work platforms, to prepare for NASA’s Journey to Mars.

Platform B North Installation

NASA Image and Video Library

2016-12-16

A construction worker solders a section of steel during the installation of the second half of the B-level work platforms, B north, for NASA's Space Launch System (SLS) rocket, in High Bay 3 in the Vehicle Assembly Building (VAB) at NASA's Kennedy Space Center in Florida. Construction workers will secure the large bolts that hold the platform in place on the north wall. The B platforms are the ninth of 10 levels of work platforms that will surround and provide access to the SLS rocket and Orion spacecraft for Exploration Mission 1. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to VAB High Bay 3, including installation of the new work platforms, to prepare for NASA’s Journey to Mars.

Structural performance of space station trusses with missing members

NASA Technical Reports Server (NTRS)

Dorsey, J. T.

1986-01-01

Structural performance of orthogonal tetrahedral and Warren-type full truss beams and platforms are compared. In addition, degradation of truss structural performance is determined for beams, platforms and a space station when individual struts are removed from the trusses. The truss beam, space station, and truss platform analytical models used in the studies are described. Stiffness degradation of the trusses due to single strut failures is determined using flexible body vibration modes. Ease of strut replacement is assessed by removing a strut and examining the truss deflection at the resulting gap due to applied forces. Finally, the reduction in truss beam strength due to a missing longeron is determined for a space station transverse boom model.

Space Station Freedom electrical power system hardware commonality with the United States Polar Platform

NASA Technical Reports Server (NTRS)

Rieker, Lorra L.; Haraburda, Francis M.

1989-01-01

The National Aeronautics and Space Administration has adopted the policy to achieve the maximum practical level of commonality for the Space Station Freedom program in order to significantly reduce life cycle costs. Commonality means using identical or similar hardware/software for meeting common sets of functionally similar requirements. Information on how the concept of commonality is being implemented with respect to electric power system hardware for the Space Station Freedom and the U.S. Polar Platform is presented. Included is a historical account of the candidate common items which have the potential to serve the same power system functions on both Freedom and the Polar Platform.

Cabana Multi-User Spaceport Tour of KSC

NASA Image and Video Library

2017-02-17

Members of the news media view the 10 levels of new work platforms in High Bay 3 inside the Vehicle Assembly Building (VAB) during a tour of NASA's Kennedy Space Center in Florida with Center Director Bob Cabana. The final platform, A north, was recently installed. The platforms will surround the Space Launch System and Orion spacecraft on the mobile launcher during processing to prepare for the first test flight. The Ground Systems Development and Operations Program is overseeing upgrades to the VAB, including installation of the new work platforms.

Orbital Spacecraft Consumables Resupply System (OSCRS): Monopropellant application to space station and OMV automatic refueling impacts of an ELV launch, volume 4

NASA Technical Reports Server (NTRS)

1987-01-01

The use of orbital spacecraft consumables resupply system (OSCRS) at the Space Station is investigated, its use with the orbital maneuvering vehicle, and launch of the OSCRS on an expendable launch vehicles. A system requirements evaluation was performed initially to identify any unique requirements that would impact the design of OSCRS when used at the Space Station. Space Station documents were reviewed to establish requirements and to identify interfaces between the OSCRS, Shuttle, and Space Station, especially the Servicing Facility. The interfaces between OSCRS and the Shuttle consists of an avionics interface for command and control and a structural interface for launch support and for grappling with the Shuttle Remote Manipulator System. For use of the OSCRS at the Space Station, three configurations were evaluated using the results of the interface definition to increase the efficiency of OSCRS and to decrease the launch weight by Station-basing specific OSCRS subsystems. A modular OSCRS was developed in which the major subsystems were Station-based where possible. The configuration of an OSCRS was defined for transport of water to the Space Station.

Space Debris and Space Safety - Looking Forward

NASA Astrophysics Data System (ADS)

Ailor, W.; Krag, H.

Man's activities in space are creating a shell of space debris around planet Earth which provides a growing risk of collision with operating satellites and manned systems. Including both the larger tracked objects and the small, untracked debris, more than 98% of the estimated 600,000 objects larger than 1 cm currently in orbit are “space junk”--dead satellites, expended rocket stages, debris from normal operations, fragments from explosions and collisions, and other material. Recognizing the problem, space faring nations have joined together to develop three basic principles for minimizing the growth of the debris population: prevent on-orbit breakups, remove spacecraft and orbital stages that have reached the end of their mission operations from the useful densely populated orbit regions, and limit the objects released during normal operations. This paper provides an overview of what is being done to support these three principles and describes proposals that an active space traffic control service to warn satellite operators of pending collisions with large objects combined with a program to actively remove large objects may reduce the rate of future collisions. The paper notes that cost and cost effectiveness are important considerations that will affect the evolution of such systems.

Electrical Power Systems for NASA's Space Transportation Program

NASA Technical Reports Server (NTRS)

Lollar, Louis F.; Maus, Louis C.

1998-01-01

Marshall Space Flight Center (MSFC) is the National Aeronautics and Space Administration's (NASA) lead center for space transportation systems development. These systems include earth to orbit launch vehicles, as well as vehicles for orbital transfer and deep space missions. The tasks for these systems include research, technology maturation, design, development, and integration of space transportation and propulsion systems. One of the key elements in any transportation system is the electrical power system (EPS). Every transportation system has to have some form of electrical power and the EPS for each of these systems tends to be as varied and unique as the missions they are supporting. The Preliminary Design Office (PD) at MSFC is tasked to perform feasibility analyses and preliminary design studies for new projects, particularly in the space transportation systems area. All major subsystems, including electrical power, are included in each of these studies. Three example systems being evaluated in PD at this time are the Liquid Fly Back Booster (LFBB) system, the Human Mission to Mars (HMM) study, and a tether based flight experiment called the Propulsive Small Expendable Deployer System (ProSEDS). These three systems are in various stages of definition in the study phase.

Public school teachers in the U.S. evaluate the educational impact of student space experiments launched by expendable vehicles, aboard Skylab, and aboard Space Shuttle.

PubMed

Burkhalter, B B; McLean, J E; Curtis, J P; James, G S

1991-12-01

Space education is a discipline that has evolved at an unprecedented rate over the past 25 years. Although program proceedings, research literature, and historical documentation have captured fragmented pieces of information about student space experiments, the field lacks a valid comprehensive study that measures the educational impact of sounding rockets, Skylab, Ariane, AMSAT, and Space Shuttle. The lack of this information is a problem for space educators worldwide which led to a national study with classroom teachers. Student flown experiments continue to offer a unique experiential approach to teach students thinking and reasoning skills that are imperative in the current international competitive environment in which they live and will work. Understanding the history as well as the current status and educational spin-offs of these experimental programs strengthens the teaching capacity of educators throughout the world to develop problem solving skills and various higher mental processes in the schools. These skills and processes enable students to use their knowledge more effectively and efficiently long after they leave the classroom. This paper focuses on student space experiments as a means of motivating students to meet this educational goal successfully.

KSC-00pp0598

NASA Image and Video Library

2000-04-27

The one-man submarine dubbed DeepWorker 2000 sits on the deck of Liberty Star, one of two KSC solid rocket booster recovery ships. Inside the sub is the pilot, Anker Rasmussen. The sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program

KSC00pp0598

NASA Image and Video Library

2000-04-27

The one-man submarine dubbed DeepWorker 2000 sits on the deck of Liberty Star, one of two KSC solid rocket booster recovery ships. Inside the sub is the pilot, Anker Rasmussen. The sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program

Manned systems utilization analysis (study 2.1). Volume 3: LOVES computer simulations, results, and analyses

NASA Technical Reports Server (NTRS)

Stricker, L. T.

1975-01-01

The LOVES computer program was employed to analyze the geosynchronous portion of the NASA's 1973 automated satellite mission model from 1980 to 1990. The objectives of the analyses were: (1) to demonstrate the capability of the LOVES code to provide the depth and accuracy of data required to support the analyses; and (2) to tradeoff the concept of space servicing automated satellites composed of replaceable modules against the concept of replacing expendable satellites upon failure. The computer code proved to be an invaluable tool in analyzing the logistic requirements of the various test cases required in the tradeoff. It is indicated that the concept of space servicing offers the potential for substantial savings in the cost of operating automated satellite systems.

Report on cost/pricing relationships for the space shuttle. [NASA/STS Operations Report

NASA Technical Reports Server (NTRS)

1977-01-01

The operations cost for the shuttle is the basis for developing the user charge policy for the system. The policy contains several elements that are significant to the user and to NASA. It will encourage the full use of the system to the benefits of the U.S. The charge policy will encourage early transition from the expendable launch vehicles to the shuttle and this will result in lower user costs for government as well as commercial users. The relationship between the charge policy and the utilization of the shuttle is critical to the economic efficiency of the system. NASA recognizes the challenging a relationship between pricing the cost of using a reusable space system, and the need to make sure it is re-used often.

Space Shuttle Projects

NASA Image and Video Library

2001-01-01

The Space Shuttle represented an entirely new generation of space vehicles, the world's first reusable spacecraft. Unlike earlier expendable rockets, the Shuttle was designed to be launched over and over again and would serve as a system for ferrying payloads and persornel to and from Earth orbit. The Shuttle's major components are the orbiter spacecraft; the three main engines, with a combined thrust of more than 1.2 million pounds; the huge external tank (ET) that feeds the liquid hydrogen fuel and liquid oxygen oxidizer to the three main engines; and the two solid rocket boosters (SRB's), with their combined thrust of some 5.8 million pounds, that provide most of the power for the first two minutes of flight. Crucially involved with the Space Shuttle program virtually from its inception, the Marshall Space Flight Center (MSFC) played a leading role in the design, development, testing, and fabrication of many major Shuttle propulsion components. The MSFC was assigned responsibility for developing the Shuttle orbiter's high-performance main engines, the most complex rocket engines ever built. The MSFC was also responsible for developing the Shuttle's massive ET and the solid rocket motors and boosters.

Space Shuttle Projects

NASA Image and Video Library

1975-01-01

The Space Shuttle represented an entirely new generation of space vehicle, the world's first reusable spacecraft. Unlike earlier expendable rockets, the Shuttle was designed to be launched over and over again and would serve as a system for ferrying payloads and persornel to and from Earth orbit. The Shuttle's major components are the orbiter spacecraft; the three main engines, with a combined thrust of more than 1.2 million pounds; the huge external tank (ET) that feeds the liquid hydrogen fuel and liquid oxygen oxidizer to the three main engines; and the two solid rocket boosters (SRB's), with their combined thrust of some 5.8 million pounds. The SRB's provide most of the power for the first two minutes of flight. Crucially involved with the Space Shuttle program virtually from its inception, the Marshall Space Flight Center (MSFC) played a leading role in the design, development, testing, and fabrication of many major Shuttle propulsion components. The MSFC was assigned responsibility for developing the Shuttle orbiter's high-performance main engines, the most complex rocket engines ever built. The MSFC was also responsible for developing the Shuttle's massive ET and the solid rocket motors and boosters.

Assessment of mixed fleet potential for space station launch and assembly

NASA Technical Reports Server (NTRS)

Deryder, L. J. (Editor)

1987-01-01

Reductions in expected STS flight rates of the Space Shuttle since the 51-L accident raise concerns about the ability of available launch capacity to meet both payload-to-orbit and crew rotation requirements for the Space Station. In addition, it is believed that some phases of Station build-up could be expedited using unmanned launch systems with significantly greater lift capacity than the STS. Examined is the potential use of expendable launch vehicles (ELVs), yet-to-be-developed unmanned shuttle-derived vehicles (SDVs), and international launch vehicles for meeting overall launch requirements to meet Space Station program objectives as defined by the 1986 Critical Evaluation Task Force (CETF). The study concludes that use of non-STS transportation can help meet several important program objectives as well as reduce the total number of STS flights. It also finds, however, that reduction of Space Station-dedicated STS flights below 8 per year forces a reduction in Station crew size assuming the CETF 90 day crew stay time baseline and seriously impairs scientific utilization of the Station.

Identification and status of design improvements to the NASA Shuttle EMU for International Space Station application.

PubMed

Wilde, R C; McBarron, J W; Faszcza, J J

1997-06-01

To meet the significant increase in EVA demand to support assembly and operations of the International Space Station (ISS), NASA and industry have improved the current Shuttle Extravehicular Mobility Unit (EMU), or "space suit", configuration to meet the unique and specific requirements of an orbital-based system. The current Shuttle EMU was designed to be maintained and serviced on the ground between frequent Shuttle flights. ISS will require the EMUs to meet increased EVAs out of the Shuttle Orbiter and to remain on orbit for up to 180 days without need for regular return to Earth for scheduled maintenance or refurbishment. Ongoing Shuttle EMU improvements have increased reliability, operational life and performance while minimizing ground and on-orbit maintenance cost and expendable inventory. Modifications to both the anthropomorphic mobility elements of the Space Suit Assembly (SSA) as well as to the Primary Life Support System (PLSS) are identified and discussed. This paper also addresses the status of on-going Shuttle EMU improvements and summarizes the approach for increasing interoperability of the U.S. and Russian space suits to be utilized aboard the ISS.

Functional Requirements for Onboard Management of Space Shuttle Consumables. Volume 2

NASA Technical Reports Server (NTRS)

Graf, P. J.; Herwig, H. A.; Neel, L. W.

1973-01-01

This report documents the results of the study "Functional Requirements for Onboard Management of Space Shuttle Consumables." The study was conducted for the Mission Planning and Analysis Division of the NASA Lyndon B. Johnson Space Center, Houston, Texas, between 3 July 1972 and 16 November 1973. The overall study program objective was two-fold. The first objective was to define a generalized consumable management concept which is applicable to advanced spacecraft. The second objective was to develop a specific consumables management concept for the Space Shuttle vehicle and to generate the functional requirements for the onboard portion of that concept. Consumables management is the process of controlling or influencing the usage of expendable materials involved in vehicle subsystem operation. The report consists of two volumes. Volume I presents a description of the study activities related to general approaches for developing consumable management, concepts for advanced spacecraft applications, and functional requirements for a Shuttle consumables management concept. Volume II presents a detailed description of the onboard consumables management concept proposed for use on the Space Shuttle.

High-Capacity Spacesuit Evaporator Absorber Radiator (SEAR)

NASA Technical Reports Server (NTRS)

Izenson, Michael G.; Chen, Weibo; Phillips, Scott; Chepko, Ariane; Bue, Grant; Quinn, Gregory

2015-01-01

Future human space exploration missions will require advanced life support technology that can operate across a wide range of applications and environments. Thermal control systems for space suits and spacecraft will need to meet critical requirements for water conservation and multifunctional operation. This paper describes a Space Evaporator Absorber Radiator (SEAR) that has been designed to meet performance requirements for future life support systems. A SEAR system comprises a lithium chloride absorber radiator (LCAR) for heat rejection coupled with a space water membrane evaporator (SWME) for heat acquisition. SEAR systems provide heat pumping to minimize radiator size, thermal storage to accommodate variable environmental conditions, and water absorption to minimize use of expendables. We have built and tested a flight-like, high-capacity LCAR, demonstrated its performance in thermal vacuum tests, and explored the feasibility of an ISS demonstration test of a SEAR system. The new LCAR design provides the same cooling capability as prior LCAR prototypes while enabling over 30% more heat absorbing capacity. Studies show that it should be feasible to demonstrate SEAR operation in flight by coupling with an existing EMU on the space station.

High-Capacity Spacesuit Evaporator Absorber Radiator (SEAR)

NASA Technical Reports Server (NTRS)

Izenson, Michael G.; Chen, Weibo; Phillips, Scott; Chepko, Ariane; Bue, Grant; Quinn, Gregory

2014-01-01

Future human space exploration missions will require advanced life support technology that can operate across a wide range of applications and environments. Thermal control systems for space suits and spacecraft will need to meet critical requirements for water conservation and adaptability to highly variable thermal environments. This paper describes a Space Evaporator Absorber Radiator (SEAR) that has been designed to meet performance requirements for future life support systems. A SEAR system comprises a lithium chloride absorber radiator (LCAR) for heat rejection coupled with a space water membrane evaporator (SWME) for heat acquisition. SEAR systems provide heat pumping to minimize radiator size, thermal storage to accommodate variable environmental conditions, and water absorption to minimize use of expendables. We have built and tested a flightlike, high-capacity LCAR, demonstrated its performance in thermal vacuum tests, and explored the feasibility of an ISS demonstration test of a SEAR system. The new LCAR design provides the same cooling capability as prior LCAR prototypes while enabling over 30% more heat absorbing capacity. Studies show that it should be feasible to demonstrate SEAR operation in flight by coupling with an existing EMU on the space station.

In-Space Internet-Based Communications for Space Science Platforms Using Commercial Satellite Networks

NASA Technical Reports Server (NTRS)

Kerczewski, Robert J.; Bhasin, Kul B.; Fabian, Theodore P.; Griner, James H.; Kachmar, Brian A.; Richard, Alan M.

1999-01-01

The continuing technological advances in satellite communications and global networking have resulted in commercial systems that now can potentially provide capabilities for communications with space-based science platforms. This reduces the need for expensive government owned communications infrastructures to support space science missions while simultaneously making available better service to the end users. An interactive, high data rate Internet type connection through commercial space communications networks would enable authorized researchers anywhere to control space-based experiments in near real time and obtain experimental results immediately. A space based communications network architecture consisting of satellite constellations connecting orbiting space science platforms to ground users can be developed to provide this service. The unresolved technical issues presented by this scenario are the subject of research at NASA's Glenn Research Center in Cleveland, Ohio. Assessment of network architectures, identification of required new or improved technologies, and investigation of data communications protocols are being performed through testbed and satellite experiments and laboratory simulations.

Integrated Power, Avionics, and Software (iPAS) Space Telecommunications Radio System (STRS) Radio User's Guide -- Advanced Exploration Systems (AES)

NASA Technical Reports Server (NTRS)

Roche, Rigoberto; Shalkhauser, Mary Jo Windmille

2017-01-01

The Integrated Power, Avionics and Software (IPAS) software defined radio (SDR) was implemented on the Reconfigurable, Intelligently-Adaptive Communication System (RAICS) platform, for radio development at NASA Johnson Space Center. Software and hardware description language (HDL) code were delivered by NASA Glenn Research Center for use in the IPAS test bed and for development of their own Space Telecommunications Radio System (STRS) waveforms on the RAICS platform. The purpose of this document is to describe how to setup and operate the IPAS STRS Radio platform with its delivered test waveform.

Reconfigurable, Intelligently-Adaptive, Communication System, an SDR Platform

NASA Technical Reports Server (NTRS)

Roche, Rigoberto J.; Shalkhauser, Mary Jo; Hickey, Joseph P.; Briones, Janette C.

2016-01-01

The Space Telecommunications Radio System (STRS) provides a common, consistent framework to abstract the application software from the radio platform hardware. STRS aims to reduce the cost and risk of using complex, configurable and reprogrammable radio systems across NASA missions. The NASA Glenn Research Center (GRC) team made a software defined radio (SDR) platform STRS compliant by adding an STRS operating environment and a field programmable gate array (FPGA) wrapper, capable of implementing each of the platforms interfaces, as well as a test waveform to exercise those interfaces. This effort serves to provide a framework toward waveform development onto an STRS compliant platform to support future space communication systems for advanced exploration missions. The use of validated STRS compliant applications provides tested code with extensive documentation to potentially reduce risk, cost and e ort in development of space-deployable SDRs. This paper discusses the advantages of STRS, the integration of STRS onto a Reconfigurable, Intelligently-Adaptive, Communication System (RIACS) SDR platform, and the test waveform and wrapper development e orts. The paper emphasizes the infusion of the STRS Architecture onto the RIACS platform for potential use in next generation flight system SDRs for advanced exploration missions.

A High-power Electric Propulsion Test Platform in Space

NASA Technical Reports Server (NTRS)

Petro, Andrew J.; Reed, Brian; Chavers, D. Greg; Sarmiento, Charles; Cenci, Susanna; Lemmons, Neil

2005-01-01

This paper will describe the results of the preliminary phase of a NASA design study for a facility to test high-power electric propulsion systems in space. The results of this design study are intended to provide a firm foundation for subsequent detailed design and development activities leading to the deployment of a valuable space facility. The NASA Exploration Systems Mission Directorate is sponsoring this design project. A team from the NASA Johnson Space Center, Glenn Research Center, the Marshall Space Flight Center and the International Space Station Program Office is conducting the project. The test facility is intended for a broad range of users including government, industry and universities. International participation is encouraged. The objectives for human and robotic exploration of space can be accomplished affordably, safely and effectively with high-power electric propulsion systems. But, as thruster power levels rise to the hundreds of kilowatts and up to megawatts, their testing will pose stringent and expensive demands on existing Earth-based vacuum facilities. These considerations and the human access to near-Earth space provided by the International Space Station (ISS) have led to a renewed interest in space testing. The ISS could provide an excellent platform for a space-based test facility with the continuous vacuum conditions of the natural space environment and no chamber walls to modify the open boundary conditions of the propulsion system exhaust. The test platform could take advantage of the continuous vacuum conditions of the natural space environment. Space testing would provide open boundary conditions without walls, micro-gravity and a realistic thermal environment. Testing on the ISS would allow for direct observation of the test unit, exhaust plume and space-plasma interactions. When necessary, intervention by on-board personnel and post-test inspection would be possible. The ISS can provide electrical power, a location for diagnostic instruments, data handling and thermal control. The platform will be designed to accommodate the side-by-side testing of multiple types of electric thrusters. It is intended to be a permanent facility in which different thrusters can be tested over time. ISS crews can provide maintenance for the platform and change out thruster test units as needed. The primary objective of this platform is to provide a test facility for electric propulsion devices of interest for future exploration missions. These thrusters are expected to operate in the range of hundreds of kilowatts and above. However, a platform with this capability could also accommodate testing of thrusters that require much lower power levels. Testing at the higher power levels would be accomplished by using power fiom storage devices on the platform, which would be gradually recharged by the ISS power generation system. This paper will summarize the results of the preliminary phase of the study with an explanation of the user requirements and the initial conceptual design. The concept for test operations will also be described. The NASA project team is defining the requirements but they will also reflect the inputs of the broader electric propulsion community including those at universities, commercial enterprises and other government laboratories. As a facility on the International Space Station, the design requirements are also intended to encompass the needs of international users. Testing of electric propulsion systems on the space station will help advance the development of systems needed for exploration and could also serve the needs of other customers. Propulsion systems being developed for commercial and military applications could be tested and certification testing of mature thrusters could be accomplished in the space environment.

[The use of the new loads of expendable medical supplies by the medical service of the Armed Forces].

PubMed

Miroshnichenko, Iu V; Bunin, S A; Grebeniuk, A N; Kononov, V N; Sidorov, D A

2014-09-01

The new loads of expendable medical supplies adopted by the Armed Forces of the Russian Federation and included into regulating documents are the most important elements of the authorized equipment system. Nine loads of expendable medical supplies, combined into two classification groups, are provided for the medical service. The use of these loads improves the effectiveness of medical supply for all stages of medical evacuation, medical continuity during medical and evacuation procedures and allows to deliver medical aid to patients on the basis of modern and innovative medical technologies.

A Study of Covert Communications in Space Platforms Hosting Government Payloads

DTIC Science & Technology

2015-02-01

possible adversarial actions (e.g., malicious software co- resident on the commercial host). Threats to the commercial supply chain are just one... supply chain to either create or exploit channel vulnerabilities. For government hosted payload missions, the critical payload data are encrypted...access to space by hosting government- supplied payloads on commercial space platforms. These commercially hosted payloads require stringent

Design summary of a geostationary facility utilized as a communications platform

NASA Technical Reports Server (NTRS)

Barberis, N. J.; Brown, J. V.

1986-01-01

This paper describes the technical aspects of a geostationary platform facility that makes maximum use of the planned NASA space station and its elements, mainly the orbital maneuvering vehicle (OMV) and the orbital transfer vehicles (OTV). The platform design concept is described, with emphasis on the key technologies utilized to configure the platform. Key systems aspects include a design summary with discussion of the controls, telemetry, command and ranging, power, propulsion, control electronics, thermal control subsystems, and space station interfaces. The use of the facility as a communications platform is developed to demonstrate the attractiveness of the concept. The economic benefits are discussed, as well as the concept of servicing for payload upgrade.

Platform C South Arrival

NASA Image and Video Library

2016-08-05

A heavy load transport truck from Tillett Heavy Hauling in Titusville, Florida, arrives at the Vehicle Assembly Building (VAB) at NASA’s Kennedy Space Center in Florida, carrying the second section of the first half of the C-level work platforms, C South, for the agency’s Space Launch System (SLS) rocket. The platform will be offloaded in the VAB staging area in the west parking lot. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to VAB High Bay 3 to support processing of the SLS and Orion spacecraft. A total of 10 levels of new platforms, 20 platform halves altogether, will surround the SLS rocket and Orion spacecraft and provide access for testing and processing.

Platform C South Arrival

NASA Image and Video Library

2016-08-04

A heavy load transport truck from Tillett Heavy Hauling in Titusville, Florida, arrives at the Vehicle Assembly Building (VAB) at NASA’s Kennedy Space Center in Florida, carrying a section of the first half of the C-level work platforms, C south, for the agency’s Space Launch System (SLS) rocket. The platform will be delivered to the VAB staging area in the west parking lot. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to VAB High Bay 3 to support processing of the SLS and Orion spacecraft. A total of 10 levels of new platforms, 20 platform halves altogether, will surround the SLS rocket and Orion spacecraft and provide access for testing and processing.

VAB Platform K(2) Lift & Install into Highbay 3

NASA Image and Video Library

2016-03-07

A 250-ton crane is used to lower the second half of the K-level work platforms for NASA’s Space Launch System (SLS) rocket into High Bay 3 inside the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. The platform will be secured about 86 feet above the VAB floor, on tower E of the high bay. The K work platforms will provide access to the SLS core stage and solid rocket boosters during processing and stacking operations on the mobile launcher. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to High Bay 3 to support processing of the SLS and Orion spacecraft. A total of 10 levels of new platforms, 20 platform halves altogether, will surround the SLS rocket and Orion spacecraft.

Modeling nuclear processes by Simulink

DOE Office of Scientific and Technical Information (OSTI.GOV)

Rashid, Nahrul Khair Alang Md, E-mail: nahrul@iium.edu.my

2015-04-29

Modelling and simulation are essential parts in the study of dynamic systems behaviours. In nuclear engineering, modelling and simulation are important to assess the expected results of an experiment before the actual experiment is conducted or in the design of nuclear facilities. In education, modelling can give insight into the dynamic of systems and processes. Most nuclear processes can be described by ordinary or partial differential equations. Efforts expended to solve the equations using analytical or numerical solutions consume time and distract attention from the objectives of modelling itself. This paper presents the use of Simulink, a MATLAB toolbox softwaremore » that is widely used in control engineering, as a modelling platform for the study of nuclear processes including nuclear reactor behaviours. Starting from the describing equations, Simulink models for heat transfer, radionuclide decay process, delayed neutrons effect, reactor point kinetic equations with delayed neutron groups, and the effect of temperature feedback are used as examples.« less

Cassini's RTGs undergo mechanical and electrical verification tests in the PHSF

NASA Technical Reports Server (NTRS)

1997-01-01

Jet Propulsion Laboratory (JPL) employees bolt a radioisotope thermoelectric generator (RTG) onto the Cassini spacecraft, at left, while other JPL workers, at right, operate the installation cart on a raised platform in the Payload Hazardous Servicing Facility (PHSF). Cassini will be outfitted with three RTGs. The power units are undergoing mechanical and electrical verification tests in the PHSF. The RTGs will provide electrical power to Cassini on its 6.7-year trip to the Saturnian system and during its four-year mission at Saturn. RTGs use heat from the natural decay of plutonium to generate electric power. The generators enable spacecraft to operate at great distances from the Sun where solar power systems are not feasible. The Cassini mission is targeted for an Oct. 6 launch aboard a Titan IVB/Centaur expendable launch vehicle. Cassini is built and managed by JPL.

KSC-97pc1065

NASA Image and Video Library

1997-07-18

Jet Propulsion Laboratory (JPL) workers prepare the installation cart (atop the platform) for removal of a radioisotope thermoelectric generator (RTG) from the adjacent Cassini spacecraft. This is the second of three RTGs being removed from Cassini after undergoing mechanical and electrical verification tests in the Payload Hazardous Servicing Facility. The third RTG to be removed is in background at left. The three RTGs will then be temporarily stored before being re-installed for flight. The RTGs will provide electrical power to Cassini on its 6.7-year trip to the Saturnian system and during its four-year mission at Saturn. RTGs use heat from the natural decay of plutonium to generate electric power. The generators enable spacecraft to operate far from the Sun where solar power systems are not feasible. The Cassini mission is scheduled for an Oct. 6 launch aboard a Titan IVB/Centaur expendable launch vehicle. Cassini is built and managed for NASA by JPL

KSC-2009-3556

NASA Image and Video Library

2009-06-05

CAPE CANAVERAL, Fla. – At the Astrotech payload processing facility in Titusville, Fla., workers prepare to move the platform on which the encapsulated GOES-O satellite sits in preparation for moving GOES-O to Cape Canaveral Air Force Station's Launch Complex 37 pad where it will be mated with the United Launch Alliance Delta IV expendable launch vehicle. The GOES-O satellite is targeted to launch no earlier than June 26. The latest Geostationary Operational Environmental Satellite, GOES-O was developed by NASA for the National Oceanic and Atmospheric Administration, or NOAA. The GOES satellites continuously provide observations of 60 percent of the Earth including the continental United States, providing weather monitoring and forecast operations as well as a continuous and reliable stream of environmental information and severe weather warnings. Once in orbit, GOES-O will be designated GOES-14, and NASA will provide on-orbit checkout and then transfer operational responsibility to NOAA. Photo credit: NASA/Jack Pfaller

KSC-2009-3557

NASA Image and Video Library

2009-06-05

CAPE CANAVERAL, Fla. – At the Astrotech payload processing facility in Titusville, Fla., workers move the platform on which the encapsulated GOES-O satellite sits in preparation for moving GOES-O to Cape Canaveral Air Force Station's Launch Complex 37 pad where it will be mated with the United Launch Alliance Delta IV expendable launch vehicle. The GOES-O satellite is targeted to launch no earlier than June 26. The latest Geostationary Operational Environmental Satellite, GOES-O was developed by NASA for the National Oceanic and Atmospheric Administration, or NOAA. The GOES satellites continuously provide observations of 60 percent of the Earth including the continental United States, providing weather monitoring and forecast operations as well as a continuous and reliable stream of environmental information and severe weather warnings. Once in orbit, GOES-O will be designated GOES-14, and NASA will provide on-orbit checkout and then transfer operational responsibility to NOAA. Photo credit: NASA/Jack Pfaller

KSC-2009-3554

NASA Image and Video Library

2009-06-05

CAPE CANAVERAL, Fla. – At the Astrotech payload processing facility in Titusville, Fla., access platforms are being removed from around the encapsulated GOES-O satellite in preparation for moving GOES-O to Cape Canaveral Air Force Station's Launch Complex 37 pad where it will be mated with the United Launch Alliance Delta IV expendable launch vehicle. The GOES-O satellite is targeted to launch no earlier than June 26. The latest Geostationary Operational Environmental Satellite, GOES-O was developed by NASA for the National Oceanic and Atmospheric Administration, or NOAA. The GOES satellites continuously provide observations of 60 percent of the Earth including the continental United States, providing weather monitoring and forecast operations as well as a continuous and reliable stream of environmental information and severe weather warnings. Once in orbit, GOES-O will be designated GOES-14, and NASA will provide on-orbit checkout and then transfer operational responsibility to NOAA. Photo credit: NASA/Jack Pfaller

KSC-2009-3555

NASA Image and Video Library

2009-06-05

CAPE CANAVERAL, Fla. – At the Astrotech payload processing facility in Titusville, Fla., access platforms are being removed from around the encapsulated GOES-O satellite in preparation for moving GOES-O to Cape Canaveral Air Force Station's Launch Complex 37 pad where it will be mated with the United Launch Alliance Delta IV expendable launch vehicle. The GOES-O satellite is targeted to launch no earlier than June 26. The latest Geostationary Operational Environmental Satellite, GOES-O was developed by NASA for the National Oceanic and Atmospheric Administration, or NOAA. The GOES satellites continuously provide observations of 60 percent of the Earth including the continental United States, providing weather monitoring and forecast operations as well as a continuous and reliable stream of environmental information and severe weather warnings. Once in orbit, GOES-O will be designated GOES-14, and NASA will provide on-orbit checkout and then transfer operational responsibility to NOAA. Photo credit: NASA/Jack Pfaller

KSC-2009-3558

NASA Image and Video Library

2009-06-05

CAPE CANAVERAL, Fla. – At the Astrotech payload processing facility in Titusville, Fla., workers move the platform on which the encapsulated GOES-O satellite sits in preparation for moving GOES-O to Cape Canaveral Air Force Station's Launch Complex 37 pad where it will be mated with the United Launch Alliance Delta IV expendable launch vehicle. The GOES-O satellite is targeted to launch no earlier than June 26. The latest Geostationary Operational Environmental Satellite, GOES-O was developed by NASA for the National Oceanic and Atmospheric Administration, or NOAA. The GOES satellites continuously provide observations of 60 percent of the Earth including the continental United States, providing weather monitoring and forecast operations as well as a continuous and reliable stream of environmental information and severe weather warnings. Once in orbit, GOES-O will be designated GOES-14, and NASA will provide on-orbit checkout and then transfer operational responsibility to NOAA. Photo credit: NASA/Jack Pfaller

Kodak Mirror Assembly Tested at Marshall Space Flight Center

NASA Technical Reports Server (NTRS)

2003-01-01

The Eastman-Kodak mirror assembly is being tested for the James Webb Space Telescope (JWST) project at the X-Ray Calibration Facility at Marshall Space Flight Center (MSFC). In this photo, one of many segments of the mirror assembly is being set up inside the 24-ft vacuum chamber where it will undergo x-ray calibration tests. MSFC is supporting Goddard Space Flight Center (GSFC) in developing the JWST by taking numerous measurements to predict its future performance. The tests are conducted in a vacuum chamber cooled to approximate the super cold temperatures found in space. During its 27 years of operation, the facility has performed testing in support of a wide array of projects, including the Hubble Space Telescope (HST), Solar A, Chandra technology development, Chandra High Resolution Mirror Assembly and science instruments, Constellation X-Ray Mission, and Solar X-Ray Imager, currently operating on a Geostationary Operational Environment Satellite. The JWST is NASA's next generation space telescope, a successor to the Hubble Space Telescope, named in honor of NASA's second administrator, James E. Webb. It is scheduled for launch in 2010 aboard an expendable launch vehicle. It will take about 3 months for the spacecraft to reach its destination, an orbit of 940,000 miles in space.

VAB Platform K(2) Lift & Install into Highbay 3

NASA Image and Video Library

2016-03-07

A 250-ton crane is used to lift the second half of the K-level work platforms for NASA’s Space Launch System (SLS) rocket high above the transfer aisle inside the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. The platform is being lifted up for transfer into High Bay 3 for installation. The platform will be secured about 86 feet above the VAB floor, on tower E of the high bay. The K work platforms will provide access to the SLS core stage and solid rocket boosters during processing and stacking operations on the mobile launcher. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to High Bay 3 to support processing of the SLS and Orion spacecraft. A total of 10 levels of new platforms, 20 platform halves altogether, will surround the SLS rocket and Orion spacecraft.

Rocket Science: The Shuttle's Main Engines, though Old, Are not Forgotten in the New Exploration Initiative

NASA Technical Reports Server (NTRS)

Covault, Craig

2005-01-01

The Space Shuttle Main Engine (SSME), developed 30 years ago, remains a strong candidate for use in the new Exploration Initiative as part of a shuttle-derived heavy-lift expendable booster. This is because the Boeing-Rocket- dyne man-rated SSME remains the most highly efficient liquid rocket engine ever developed. There are only enough parts for 12-15 existing SSMEs, however, so one NASA option is to reinitiate SSME production to use it as a throw-away, as opposed to a reusable, powerplant for NASA s new heavy-lift booster.

Stress Prediction System

NASA Technical Reports Server (NTRS)

1995-01-01

NASA wanted to know how astronauts' bodies would react under various gravitational pulls and space suit weights. Under contract to NASA, the University of Michigan's Center for Ergonomics developed a model capable of predicting what type of stress and what degree of load a body could stand. The algorithm generated was commercialized with the ISTU (Isometric Strength Testing Unit) Functional Capacity Evaluation System, which simulates tasks such as lifting a heavy box or pushing a cart and evaluates the exertion expended. It also identifies the muscle group that limits the subject's performance. It is an effective tool of personnel evaluation, selection and job redesign.

A Low Fidelity Simulation To Examine The Design Space For An Expendable Active Decoy

DTIC Science & Technology

2017-12-01

Postgraduate School Monterey, CA 93943-5000 8. PERFORMING ORGANIZATION REPORT NUMBER 9. SPONSORING /MONITORING AGENCY NAME(S) AND ADDRESS(ES) N ...discussed in Aircraft Model Section III.E), and read the associated integration improvement factor off the left side of Figure 10. b p b s f n ...V0 is the root mean squared noise level.   2 2 0 2 2 0 V V N V p V e V        (18) The probability density function for Gaussian noise is

Transferring technology to the public sector.

NASA Technical Reports Server (NTRS)

Alper, M. E.

1972-01-01

Approximately four years ago the Jet Propulsion Laboratory, under NASA sponsorship, began to devote some of its resources to examining ways to transfer space technology to the civil sector. As experience accumulated under this program, certain principles basic to success in technology transfer became apparent. An adequate definition of each problem must be developed before any substantial effort is expended on a solution. In most instances, a source of funds other than the potential user is required to support the problem definition phase of the work. Sensitivity to the user's concerns and effective interpersonal communications between the user and technical personnel are essential to success.

KSC-03pd0517

NASA Image and Video Library

2003-02-19

KENNEDY SPACE CENTER, FLA. -- - At NASA's Family & Community Mars Exploration Day, held in Cape Canaveral, Fla., Kristie Durham (left), Martha Vreeland (center), and Jeanne Hawkins (right), with Expendable Launch Vehicle Services, offer information about the facility. The event informed students and the general public about Florida's key role as NASA's "Gateway to Mars" and offered an opportunity to meet with scientists, engineers, educators and others working Mars exploration missions. The Mars Exploration Rovers are being prepared for launch this spring aboard Boeing Delta II rockets from the Cape Canaveral Air Force Station. They will land on Mars and start exploring in January 2004.

KSC-03PD-0517

NASA Technical Reports Server (NTRS)

2003-01-01

KENNEDY SPACE CENTER, FLA. -- - At NASA's Family & Community Mars Exploration Day, held in Cape Canaveral, Fla., Kristie Durham (left), Martha Vreeland (center), and Jeanne Hawkins (right), with Expendable Launch Vehicle Services, offer information about the facility. The event informed students and the general public about Florida's key role as NASA's 'Gateway to Mars' and offered an opportunity to meet with scientists, engineers, educators and others working Mars exploration missions. The Mars Exploration Rovers are being prepared for launch this spring aboard Boeing Delta II rockets from the Cape Canaveral Air Force Station. They will land on Mars and start exploring in January 2004.

The Standard Deviation of Launch Vehicle Environments

NASA Technical Reports Server (NTRS)

Yunis, Isam

2005-01-01

Statistical analysis is used in the development of the launch vehicle environments of acoustics, vibrations, and shock. The standard deviation of these environments is critical to accurate statistical extrema. However, often very little data exists to define the standard deviation and it is better to use a typical standard deviation than one derived from a few measurements. This paper uses Space Shuttle and expendable launch vehicle flight data to define a typical standard deviation for acoustics and vibrations. The results suggest that 3dB is a conservative and reasonable standard deviation for the source environment and the payload environment.

KSC-97PC1110

NASA Image and Video Library

1997-07-22

Flight mechanics from NASA’s Jet Propulsion Laboratory (JPL) in Pasadena, Calif., lower the Cassini spacecraft onto its launch vehicle adapter in KSC’s Payload Hazardous Servicing Facility. The adapter will later be mated to a Titan IV/Centaur expendable launch vehicle that will lift Cassini into space. Scheduled for launch in October, the Cassini mission, a joint US-European four-year orbital surveillance of Saturn's atmosphere and magnetosphere, its rings, and its moons, seeks insight into the origins and evolution of the early solar system. It will take seven years for the spacecraft to reach Saturn. JPL is managing the Cassini project for NASA

Definition and design of an experiment to test raster scanning with rotating unbalanced-mass devices on gimbaled payloads

NASA Technical Reports Server (NTRS)

Lightsey, W. D.; Alhorn, D. C.; Polites, M. E.

1992-01-01

An experiment designed to test the feasibility of using rotating unbalanced-mass (RUM) devices for line and raster scanning gimbaled payloads, while expending very little power is described. The experiment is configured for ground-based testing, but the scan concept is applicable to ground-based, balloon-borne, and space-based payloads, as well as free-flying spacecraft. The servos used in scanning are defined; the electronic hardware is specified; and a computer simulation model of the system is described. Simulation results are presented that predict system performance and verify the servo designs.

RS-25 for the NASA Cargo Launch Vehicle: The Evolution of SSME for Space Exploration

NASA Technical Reports Server (NTRS)

Kynard, Michael H.; McArthur, J. Craig; Ise, Dayna S.

2006-01-01

A key element of the National Vision for Space Exploration is the development of a heavy-lift Cargo Launch Vehicle (CaLV). Missions to the Moon, Mars, and beyond are only possible with the logistical capacity of putting large payloads in low-earth orbit. However, beyond simple logistics, there exists the need for this capability to be as cost effective as possible to ensure mission sustainability. An element of the CaLV project is, therefore, the development of the RS-25, which represents the evolution of the proven Space Shuttle Main Engine (SSME) into a high-performance, cost-effective expendable rocket engine. The development of the RS-25 will be built upon the foundation of over one million seconds of accumulated hot-fire time on the SSME. Yet in order to transform the reusable SSME into the more cost-effective, expendable RS-25 changes will have to be made. Thus the project will inevitably strive to maintain a balance between demonstrated heritage products and processes and the utilization of newer technology developments. Towards that end, the Core Stage Engine Office has been established at the NASA Marshall Space Flight Center to initiate the design and development of the RS-25 engine. This paper is being written very early in the formulation phase of the RS-25 project. Therefore the focus of this paper will be to present the scope, challenges, and opportunities for the RS-25 project. Early schedules and development decisions and plans will be explained. For not only must the RS-25 project achieve cost effectiveness through the development of new, evolved components such as a channel-wall nozzle, a new HIP-bonded main combustion chamber, and several others, it must simultaneously develop the means whereby this engine can be manufactured on a scale never envisioned for the SSME. Thus, while the overall project will span the next eight to ten years, there is little doubt that even this schedule is aggressive with a great deal of work to accomplish.

Platform C South Arrival

NASA Image and Video Library

2016-08-05

The second section of the first half of the C-level work platforms, C South, for NASA’s Space Launch System (SLS) rocket was offloaded from a heavy transport truck in a staging area on the west side of the Vehicle Assembly Building (VAB) at the agency’s Kennedy Space Center in Florida. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to VAB High Bay 3 to support processing of the SLS and Orion spacecraft. A total of 10 levels of new platforms, 20 platform halves altogether, will surround the SLS rocket and Orion spacecraft and provide access for testing and processing.

Erectable space platform for space sciences and applications

NASA Technical Reports Server (NTRS)

1979-01-01

The specific objectives of the study were to: (1) identify a viable conceptual design for the service module/platform; (2) assess the technology issues that must be faced in planning development; and (3) prepare an initial plan for bringing critical technologies up to acceptable levels.

Evolutionary space platform concept study. Volume 3: Programmatics for manned space platform concepts

NASA Technical Reports Server (NTRS)

1982-01-01

The programmatic data for the reference concept of the Manned Space Platform is presented. Details regarding work breakdown structure (WBS) and dictionary, the facilities and equipment required to produce the modules, the project schedule and logic diagram, a preliminary assessment of environmental impacts and details regarding the estimated costs for the reference concept are included. The proposed WBS which was developed to provide summary and system level segregation of the nonrecurring and recurring portions of the Manned Space Platform project is also included. The accompanying dictionary outlines the function and activities contained within each WBS element. The facility and equipment required to produce the various modules is discussed. Generally, required equipment is within the existing state of the art although the size of some of the items to be manufactured is a consideration. A preliminary manufacturing flow was also provided. The project schedules presented consist of the Master Project Summary Schedule, the Master Project Phasing Chart and the Logic Network.

Study to identify future cryogen payload elements/users for space shuttle launch during period 1990 to 2000

NASA Technical Reports Server (NTRS)

Elim, Frank M.

1989-01-01

This study provides a summary of future cryogenic space payload users, their currently projected needs and reported planning for space operations over the next decade. At present, few users with payloads consisting of reactive cryogens, or any cryogen in significant quantities, are contemplating the use of the Space Shuttle. Some members of the cryogenic payload community indicated an interest in flying their future planned payloads on the orbiter, versus an expendable launch vehicle (ELV), but are awaiting the outcome of a Rockwell study to define what orbiter mods and payloads requirements are needed to safely fly chemically reactive cryogen payloads, and the resultant cost, schedule, and operational impacts. Should NASA management decide in early 1990 to so modify orbiter(s), based on the Rockwell study and/or changes in national defense payloads launch requirements, then at least some cryo payload customers will reportedly plan on using the Shuttle orbiter vehicle in preference to an ELV. This study concludes that the most potential for possible future cryogenic space payloads for the Space Transportation System Orbiter fleet lies within the scientific research and defense communities.

Safety And Promotion in the Federal Aviation Administration- Enabling Safe and Successful Commercial Space Transportation

NASA Astrophysics Data System (ADS)

Repcheck, Randall J.

2010-09-01

The United States Federal Aviation Administration’s Office of Commercial Space Transportation(AST) authorizes the launch and reentry of expendable and reusable launch vehicles and the operation of launch and reentry sites by United States citizens or within the United States. It authorizes these activities consistent with public health and safety, the safety of property, and the national security and foreign policy interests of the United States. In addition to its safety role, AST has the role to encourage, facilitate, and promote commercial space launches and reentries by the private sector. AST’s promotional role includes, among other things, the development of information of interest to industry, the sharing of information of interest through a variety of methods, and serving as an advocate for Commercial Space Transportation within the United States government. This dual safety and promotion role is viewed by some as conflicting. AST views these two roles as complementary, and important for the current state of commercial space transportation. This paper discusses how maintaining a sound safety decision-making process, maintaining a strong safety culture, and taking steps to avoid complacency can together enable safe and successful commercial space transportation.

Control of NASA's Space Launch System

NASA Technical Reports Server (NTRS)

VanZwieten, Tannen S.

2014-01-01

The flight control system for the NASA Space Launch System (SLS) employs a control architecture that evolved from Saturn, Shuttle & Ares I-X while also incorporating modern enhancements. This control system, baselined for the first unmanned launch, has been verified and successfully flight-tested on the Ares I-X rocket and an F/A-18 aircraft. The development of the launch vehicle itself came on the heels of the Space Shuttle retirement in 2011, and will deliver more payload to orbit and produce more thrust than any other vehicle, past or present, opening the way to new frontiers of space exploration as it carries the Orion crew vehicle, equipment, and experiments into new territories. The initial 70 metric ton vehicle consists of four RS-25 core stage engines from the Space Shuttle inventory, two 5- segment solid rocket boosters which are advanced versions of the Space Shuttle boosters, and a core stage that resembles the External Tank and carries the liquid propellant while also serving as the vehicle's structural backbone. Just above SLS' core stage is the Interim Cryogenic Propulsion Stage (ICPS), based upon the payload motor used by the Delta IV Evolved Expendable Launch Vehicle (EELV).

A 100 kW-Class Technology Demonstrator for Space Solar Power

NASA Technical Reports Server (NTRS)

Carrington, Connie; Howell, Joe; Day, Greg

2004-01-01

A first step in the development of solar power from space is the flight demonstration of critical technologies. These fundamental technologies include efficient solar power collection and generation, power management and distribution, and thermal management. In addition, the integration and utilization of these technologies into a viable satellite bus could provide an energy-rich platform for a portfolio of payload experiments such as wireless power transmission (WPT). This paper presents the preliminary design of a concept for a 100 kW-class fiee-flying platform suitable for flight demonstration of technology experiments. Recent space solar power (SSP) studies by NASA have taken a stepping stones approach that lead to the gigawatt systems necessary to cost-effectively deliver power from space. These steps start with a 100 kW-class satellite, leading to a 500 kW and then a 1 MW-class platform. Later steps develop a 100 M W bus that could eventually lead to a 1-2 GW pilot plant for SSP. Our studies have shown that a modular approach is cost effective. Modular designs include individual laser-power-beaming satellites that fly in constellations or that are autonomously assembled into larger structures at geosynchronous orbit (GEO). Microwave power-beamed approaches are also modularized into large numbers of identical units of solar arrays, power converters, or supporting structures for arrays and microwave transmitting antennas. A cost-effective approach to launching these modular units is to use existing Earth-to-orbit (ETO) launch systems, in which the modules are dropped into low Earth orbit (LEO) and then the modules perform their own orbit transfer to GEO using expendable solar arrays to power solar electric thrusters. At GEO, the modules either rendezvous and are assembled robotically into larger platforms, or are deployed into constellations of identical laser power-beaming satellites. Since solar electric propulsion by the modules is cost-effective for both self-transport of the modules from LEO to GEO, and for on-orbit stationkeeping and repositioning capability during the satellite's lifetime, this technology is also critical in technology development for SSP. The 100 kW-class technology demonstrator will utilize advanced solar power collection and generation technologies, power management and distribution, advanced thermal management, and solar electric propulsion. State-of-the-art solar concentrators, highly efficient multi-junction solar cells, integrated thermal management on the arrays, and innovative deployable structure design and packaging make the 100 kW satellite feasible for launch on one existing launch vehicle. Early SSP studies showed that a major percentage of the on-orbit mass for power-beaming satellites was from massive power converters at the solar arrays, at the bus, at the power transmitter, or at combinations of these locations. Higher voltage mays and power management and distribution (PMAD) systems reduce or eliminate the need for many of these massive power converters, and could enable direct-drive of high-voltage solar electric thrusters. Lightweight, highly efficient thermal management systems are a critical technology that must be developed and flown for SSP feasibility. Large amounts of power on satellites imply that large amounts of waste heat will need to be managed. In addition, several of the more innovative lightweight configurations proposed for SSP satellites take advantage of solar concentrators that are intractable without advanced thermal management technologies for the solar arrays. These thermal management systems include efficient interfaces with the WPT systems or other high-power technology experiments, lightweight deployable radiators that can be easily integrated into satellite buses, and efficient reliable thermal distribution systems that can pipe heat from the technology experiments to the radiators. In addition to demonstrating the integration and use of these mission-ctical technologies, the 100 kw-class satellite will provide a large experiment deck for a portfolio of technology experiments. Current plans for this technology demonstrator allow 2000 kg of payload capability and up to 100 kW of power. The technology experiments could include one or more wireless power transmission demonstrations, either to the Earth s surface or to a suitable space-based receiver. Technology experiments to quantify the on-orbit performance of critical technologies for SSP or space exploration are welcomed. In addition, the technology experiments provide an opportunity for international cooperation, to advance technology readiness levels of SSP technologies that require flight demonstration. This paper will present the preliminary design for a 100 kW solar-powered satellite and a variety of technology experiments that may be suitable for flight demonstration. In addition, a space-to-Earth-surface WPT experiment will be discussed.

The U.S. Evolved Expendable Launch Vehicle (EELV) programs : Quarterly Launch Report : special report

DOT National Transportation Integrated Search

1997-01-01

The Evolved Expendable Launch Vehicle (EELV) Program is a Department of Defense technology-development program managed by the Air Force. The program is intended to produce an improved launch vehicle family for government use. The EELV will replace th...

Large space structures controls research and development at Marshall Space Flight Center: Status and future plans

NASA Technical Reports Server (NTRS)

Buchanan, H. J.

1983-01-01

Work performed in Large Space Structures Controls research and development program at Marshall Space Flight Center is described. Studies to develop a multilevel control approach which supports a modular or building block approach to the buildup of space platforms are discussed. A concept has been developed and tested in three-axis computer simulation utilizing a five-body model of a basic space platform module. Analytical efforts have continued to focus on extension of the basic theory and subsequent application. Consideration is also given to specifications to evaluate several algorithms for controlling the shape of Large Space Structures.

Space Station Freedom electrical power system hardware commonality with the United States Polar Platform

NASA Technical Reports Server (NTRS)

Rieker, Lorra L.; Haraburda, Francis M.

1989-01-01

Information is presented on how the concept of commonality is being implemented with respect to electric power system hardware for the Space Station Freedom and the U.S. Polar Platform. Included is a historical account of the candidate common items which have the potential to serve the same power system functions on both Freedom and the Polar Platform. The Space Station program and objectives are described, focusing on the test and development responsibilities. The program definition and preliminary design phase and the design and development phase are discussed. The goal of this work is to reduce the program cost.

KSC-2009-1567

NASA Image and Video Library

2009-02-12

CAPE CANAVERAL, Fla. – An aerial view of a mobile launcher platform that is parked in the Launch Complex 39 Area at NASA's Kennedy Space Center in Florida. The platform, which is a moveable base for the launch of space shuttle, is a two-story steel structure 25 feet high, 160 feet long and 135 feet wide. It is constructed of welded steel up to 6 inches thick. The platform rests on six 22-foot-tall pedestals. Photo credit: NASA/Kim Shiflett

KSC-2009-1566

NASA Image and Video Library

2009-02-12

CAPE CANAVERAL, Fla. – An aerial view of a mobile launcher platform that is parked in the Launch Complex 39 Area at NASA's Kennedy Space Center in Florida. The platform, which is a moveable base for the launch of space shuttle, is a two-story steel structure 25 feet high, 160 feet long and 135 feet wide. It is constructed of welded steel up to 6 inches thick. The platform rests on six 22-foot-tall pedestals. Photo credit: NASA/Kim Shiflett

KSC-2009-1568

NASA Image and Video Library

2009-02-12

CAPE CANAVERAL, Fla. – An aerial view of a mobile launcher platform that is parked in the Launch Complex 39 Area at NASA's Kennedy Space Center in Florida. The platform, which is a moveable base for the launch of space shuttle, is a two-story steel structure 25 feet high, 160 feet long and 135 feet wide. It is constructed of welded steel up to 6 inches thick. The platform rests on six 22-foot-tall pedestals. Photo credit: NASA/Kim Shiflett

A Framework for Assessing the Reusability of Hardware (Reusable Rocket Engines)

NASA Technical Reports Server (NTRS)

Childress-Thompson, Rhonda; Thomas, Dale; Farrington, Philip

2016-01-01

Within the past few years, there has been a renewed interest in reusability as it applies to space flight hardware. Commercial companies such as Space Exploration Technologies Corporation (SpaceX), Blue Origin, and United Launch Alliance (ULA) are pursuing reusable hardware. Even foreign companies are pursuing this option. The Indian Space Research Organization (ISRO) launched a reusable space plane technology demonstrator and Airbus Defense and Space is planning to recover the main engines and avionics from its Advanced Expendable Launcher with Innovative engine Economy [1] [2]. To date, the Space Shuttle remains as the only Reusable Launch (RLV) to have flown repeated missions and the Space Shutte Main Engine (SSME) is the only demonstrated reusable engine. Whether the hardware being considered for reuse is a launch vehicle (fully reusable), a first stage (partially reusable), or a booster engine (single component), the overall governing process is the same; it must be recovered and recertified for flight. Therefore, there is a need to identify the key factors in determining the reusability of flight hardware. This paper begins with defining reusability to set the context, addresses the significance of reuse, and discusses areas that limit successful implementation. Finally, this research identifies the factors that should be considered when incorporating reuse.

Floor Plans Fuel Tank Support, Fuel Platform, and LOX ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Floor Plans - Fuel Tank Support, Fuel Platform, and LOX Platform Plans - Marshall Space Flight Center, F-1 Engine Static Test Stand, On Route 565 between Huntsville and Decatur, Huntsville, Madison County, AL

Space flight nutrition research: platforms and analogs

NASA Technical Reports Server (NTRS)

Smith, Scott M.; Uchakin, Peter N.; Tobin, Brian W.

2002-01-01

Conducting research during actual or simulated weightlessness is a challenging endeavor, where even the simplest activities may present significant challenges. This article reviews some of the potential obstacles associated with performing research during space flight and offers brief descriptions of current and previous space research platforms and ground-based analogs, including those for human, animal, and cell-based research. This review is intended to highlight the main issues of space flight research analogs and leave the specifics for each physiologic system for the other papers in this section.

Platform C South Arrival

NASA Image and Video Library

2016-08-04

A heavy load transport truck from Tillett Heavy Hauling in Titusville, Florida, arrives at the Vehicle Assembly Building (VAB) at NASA’s Kennedy Space Center in Florida, carrying a section of the first half of the C-level work platforms, C South, for the agency’s Space Launch System (SLS) rocket. The platform is being lifted and transferred onto support stands in the VAB staging area in the west parking lot. The Ground Systems Development and Operations Program is overseeing upgrades and modifications to VAB High Bay 3 to support processing of the SLS and Orion spacecraft. A total of 10 levels of new platforms, 20 platform halves altogether, will surround the SLS rocket and Orion spacecraft and provide access for testing and processing.

Design and Development of VHF Antennas for Space Borne Signal of Opportunity Receivers for Cubesat Platforms

NASA Technical Reports Server (NTRS)

Deshpande, Manohar; Piepmeier, Jeffrey

2015-01-01

Design and Development of VHF Antennas for Space Borne Signal of Opportunity Receivers for Cubesat Platforms. Space borne microwave remote sensors at VHF/UHF frequencies are important instruments to observe reflective properties of land surfaces through thick and heavy forestation on a global scale. One of the most cost effective ways of measuring land reflectivity at VHF/UHF frequencies is to use signals transmitted by existing communication satellites (operating at VHF/UHF band) as a signal of opportunity (SoOp) signal and passive receivers integrated with airborne/space borne platforms operating in the Low Earth Orbit (LEO). One of the critical components of the passive receiver is two antennas (one to receive only direct signal and other to receive only reflected signal) which need to have ideally high (>30dB) isolation. However, because of small size of host platforms and broad beam width of dipole antennas, achieving adequate isolation between two channels is a challenging problem and need to be solved for successful implementation of space borne SoOp technology for remote sensing. In this presentation a novel enabling VHF antenna technology for Cubesat platforms is presented to receive direct as well as reflected signal with needed isolation. The novel scheme also allows enhancing the gain of individual channels by factor of 2 without use of reflecting ground plane

The Case for Spacecrime: The Rise of Crime and Piracy in the Space Domain

DTIC Science & Technology

2013-06-01

resulted in generally outdated hardware with limited capabilities.21 More recent hardware platforms such as Arduino, BeagleBone, Raspberry Pi and others...www.citizensinspace.org; Arduino platform, http://www.arduino.cc; Beaglebone platform, http://www.beagleboard.org; Raspberry Pi platform, http

Organics in Space: Results from Space Exposure Platforms and Nanosatellites

NASA Technical Reports Server (NTRS)

Foing, B. H.; Ehrenfreund, P.; Salama, Farid; Contreras, Cesar Sanchez; Sciamma O'Brien, Ella; Bejaoui, Salma

2015-01-01

A series of successful laboratory astrophysics experiments performed on International Space Station(ISS) external platforms such as EXPOSE have provided insights into the evolution of organic and biological materials in space and planetary environments. The study of the reactions, destruction, and longevity of organics in the space environment is of fundamental interest. To provide an accurate outer space environment for extended durations, exposure experiments in low Earth orbit have been conducted in the last decades in order to examine the consequences of actual space conditions including combinations of solar and cosmic radiation, space vacuum, and microgravity. The OOREOS (OrganismORganic Exposure to Orbital Stresses) nanosatellite studied in situ during the 6-month primary and 1-year extended mission the photochemical processing of selected PAHs in low Earth orbit (650 km altitude); results were autonomously telemetered to Earth. We report on the methods and flight preparation of samples for space exposure platforms and results on the stability of organic thin-films. The UV-vis degradation process of thin-films was recorded over time, which revealed intriguing and counter-intuitive photolytic kinetics that will be re-investigated on the ISS in a space environment.

Discussion on Application of Space Materials and Technological Innovation in Dynamic Fashion Show

NASA Astrophysics Data System (ADS)

Huo, Meilin; Kim, Chul Soo; Zhao, Wenhan

2018-03-01

In modern dynamic fashion show, designers often use the latest ideas and technology, and spend their energy in stage effect and overall environment to make audience’s watching a fashion show like an audio-visual feast. With rapid development of China’s science and technology, it has become a design trend to strengthen the relationship between new ideas, new trends and technology in modern art. With emergence of new technology, new methods and new materials, designers for dynamic fashion show stage art can choose the materials with an increasingly large scope. Generation of new technology has also made designers constantly innovate the stage space design means, and made the stage space design innovated constantly on the original basis of experiences. The dynamic clothing display space is on design of clothing display space, layout, platform decoration style, platform models, performing colors, light arrangement, platform background, etc.

An Assessment of the International Space Station's Trace Contaminant Control Subassembly Process Economics

NASA Technical Reports Server (NTRS)

Perry J. L.; Cole, H. E.; El-Lessy, H. N.

2005-01-01

The International Space Station (ISS) Environmental Control and Life Support System includes equipment speci.cally designed to actively remove trace chemical contamination from the cabin atmosphere. In the U.S. on-orbit segment, this function is provided by the trace contaminant control subassembly (TCCS) located in the atmosphere revitalization subsystem rack housed in the laboratory module, Destiny. The TCCS employs expendable adsorbent beds to accomplish its function leading to a potentially signi.cant life cycle cost over the life of the ISS. Because maintaining the TCCSs proper can be logistically intensive, its performance in .ight has been studied in detail to determine where savings may be achieved. Details of these studies and recommendations for improving the TCCS s process economics without compromising its performance or crew health and safety are presented and discussed.

Design and Early In-flight Performance of the Tropical Rainfall Measuring Mission (TRMM) Power Subsystem

NASA Technical Reports Server (NTRS)

Moran, Vickie Eakin; Flatley, Thomas P.; Shue, John; Gaddy, Edward M.; Manzer, Dominic; Hicks, Edward

1998-01-01

Maryland built the spacecraft in-house with four U.S. instruments and one Japanese instrument, the first space flown Precipitation Radar (PR). The TRMM Observatory was successfully launched from Tanegashima Space Center in Japan on an H-2 Expendable Launch Vehicle on November 27, 1997. This paper presents an overview of the TRMM Power System including its design, testing, and in flight performance for the first 70 days. Finally, key lessons learned are presented. The TRMM power system consists of an 18.1 square meter deployed solar array fabricated by TRW with Tecstar GaAs/Ge cells, two (2) Hughes 50 Ampere-Hour (Ah) Super NiCd' batteries, each with 22 Eagle-Picher cells, and three (3) electronics boxes designed to provide power regulation, battery charge control, and command and telemetry interface.

Advanced Concept

NASA Image and Video Library

1999-08-13

This photograph is an artist's cutaway view of the X-37 flight demonstrator showing its components. The X-37 experimental launch vehicle is roughly 27.5 feet (8.3 meters) long and 15 feet (4.5 meters) in wingspan. Its experiment bay is 7 feet (2.1 meters) long and 4 feet (1.2 meters) in diameter. Designed to operate in both the orbital and reentry phases of flight, the X-37 will increase both safety and reliability, while reducing launch costs from $10,000 per pound to $1000 per pound. The X-37 can be carried into orbit by the Space Shuttle or be launched by an expendable rocket. Managed by Marshall Space Flight Center and built by the Boeing Company, the X-37 is scheduled to fly two orbital missions in 2002/2003 to test the reusable launch vehicle technologies.

Operationally Efficient Propulsion System Study (OEPSS): OEPSS Video Script

NASA Technical Reports Server (NTRS)

Wong, George S.; Waldrop, Glen S.; Trent, Donnie (Editor)

1992-01-01

The OEPSS video film, along with the OEPSS Databooks, provides a data base of current launch experience that will be useful for design of future expendable and reusable launch systems. The focus is on the launch processing of propulsion systems. A brief 15-minute overview of the OEPSS study results is found at the beginning of the film. The remainder of the film discusses in more detail: current ground operations at the Kennedy Space Center; typical operations issues and problems; critical operations technologies; and efficiency of booster and space propulsion systems. The impact of system architecture on the launch site and its facility infrastucture is emphasized. Finally, a particularly valuable analytical tool, developed during the OEPSS study, that will provide for the "first time" a quantitative measure of operations efficiency for a propulsion system is described.

Flight prototype CO2 and humidity control system

NASA Technical Reports Server (NTRS)

Rudy, K. M.

1977-01-01

A regenerable CO2 and humidity control system is presently being developed for potential use on the space shuttle as an alternative to the baseline lithium hydroxide system. The system utilizes a sorbent material (designated HS-C) to adsorb CO2 and water vapor from the cabin atmosphere and desorb the CO2 and water vapor overboard when exposed to a space vacuum. Continuous operation is achieved by utilizing two beds which are alternately cycled between adsorption and desorption. A shuttle vehicle integration study showed that the HS-C system offers substantial weight advantages compared to the baseline shuttle orbiter expendable lithium hydroxide CO2 removal system for extended missions beyond the nominal design of four men for seven days. This study defined a system packaging envelope in the area presently occupied by the LiOH cartridges.